An in-cabin wind tunnel test platform level system and method for high altitude performance testing of aircraft components

Abstract

The application discloses an in-cabin wind tunnel test platform level system for high-altitude performance test of an aircraft component. The platform level system adopts a platform architecture composed of an environment cabin body layer, an in-cabin wind tunnel layer, a parameter adjustment layer and a closed loop control layer, and integrates a closed circulation wind tunnel in a whole in a closed high-altitude environment simulation cabin. A temperature control module, a pressure control module and a humidity control module are used to implement integrated preprocessing of the gas entering the cabin body in terms of temperature, pressure and humidity, and a one-way valve is combined to realize boundary isolation of the parameter supply side and the cabin body and the wind tunnel coupling side. A multi-point temperature and humidity sensor array and an upper and lower partition intelligent environment homogenization fan array are used to realize consistent control of the background environment field space. A full-embedded wireless measurement and control support rod and UWB communication are used to realize high-precision measurement and sealing. The application can realize cooperative and stable maintenance of the background environment and the local test flow field under the condition of high-altitude multi-parameter coupling, and is suitable for high-altitude performance verification of aircraft components, materials and sensors.

Description

Technical Field

[0001] This invention relates to the field of aerodynamic testing equipment and environmental simulation technology, specifically to an in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components. It is particularly suitable for testing aircraft components, sensors, materials, or small unmanned aerial vehicles in high-altitude environments with multiple coupled parameters such as low air pressure, low temperature, and high humidity, to comprehensively test their aerodynamic performance, thermodynamic characteristics, and environmental adaptability. Background Technology

[0002] In the field of environmental adaptability testing for internal combustion engine intake systems, turbocharging systems, intercooling systems, and the entire engine, it is necessary to simultaneously superimpose environmental parameters such as temperature, pressure, and humidity under controlled wind speed conditions to simulate the aerodynamic and thermal environmental conditions of the engine or its components during actual service. In existing testing setups, a common configuration is a separate arrangement of the wind tunnel and the environmental chamber. This separation means that the wind speed field and the environmental parameter field are not integrated and established within the same controlled space, but rather are generated independently by different systems and then coupled.

[0003] One typical configuration is a split structure with the wind tunnel outside and the environmental chamber inside. The external wind tunnel system provides the airflow field with a set wind speed, while the test specimen is placed inside the environmental chamber, which regulates environmental parameters such as temperature, pressure, and humidity within the test space. The wind tunnel and the environmental chamber are coupled through ventilation ducts, nozzles, through-chamber interfaces, or connecting channels. In this split configuration, the kinetic energy of the airflow is mainly provided by the wind tunnel system, while the thermal environmental parameters are mainly established by the environmental chamber system. Therefore, wind speed control and temperature, pressure, and humidity control are not simultaneously formed within the same controlled volume, but are achieved collaboratively through separate systems.

[0004] Secondly, another common testing approach involves installing an air supply device inside the environmental chamber to generate a specific airflow under controlled temperature, pressure, and humidity conditions. The environmental chamber itself establishes the required temperature, pressure, and humidity environment for the test. Fans, blower units, nozzles, or flow guiding mechanisms are then arranged inside the chamber to provide localized incoming or directional airflow to the vicinity of the specimen. While this approach of installing an air supply device inside the environmental chamber allows for the simultaneous superposition of environmental parameters and airflow effects within the same chamber, the airflow generation method is essentially still limited to in-chamber air supply or localized blowing. Airflow fields with configurations including air supply devices often fail to meet the technical requirements of standard wind tunnel test flow fields. This is because in-chamber air supply systems generally lack the typical aerodynamic structures of a complete wind tunnel contraction section, rectification section, pressure stabilization section, and test section. Consequently, the airflow exhibits significant limitations in terms of velocity uniformity, flow direction consistency, turbulence control, flow field boundary stability, and repeatability. Therefore, although airflow configurations including air supply devices can create certain wind speed conditions within an environmental chamber, they are localized and auxiliary airflow fields, and cannot be equated with the precisely controllable, shapeable, low-turbulence test flow fields in a standard wind tunnel. Consequently, existing solutions involving air supply devices within environmental chambers still struggle to simultaneously meet the requirements for both environmental parameter control and high-quality airflow field construction in test scenarios involving the entire internal combustion engine, intake system, cooling module, turbocharger, and intercooler, where high-quality incoming airflow is crucial.

[0005] Thirdly, a common implementation method in existing testing systems involves conducting environmental adaptability testing and aerodynamic performance testing in separate stages and locations. One approach involves first conducting environmental adaptability tests in an environmental chamber, including high-temperature, low-temperature, high-altitude low-pressure, and high-humidity conditions, to examine the operational response of the internal combustion engine or its related components such as intake, turbocharging, and cooling systems under specific environmental parameters. The specimen is then transferred to a conventional wind tunnel for aerodynamic performance testing to assess the impact of changes in incoming flow conditions on its flow characteristics, heat transfer performance, or matching characteristics. Another approach uses the reverse process: aerodynamic testing is first conducted in a wind tunnel, followed by environmental adaptability verification in an environmental chamber. Both of these approaches essentially involve separate testing of environmental and aerodynamic loads. The environmental parameter field and the airflow field are not applied to the specimen simultaneously under the same spatiotemporal conditions. The wind field and the environmental field are not actually formed in the same physical space, on the same time scale, and under the same boundary conditions. The specimen is not subjected to actual high-altitude service conditions. While step-by-step testing can obtain test data for specimens under single environmental or aerodynamic factors, the lack of simultaneous superposition of key boundary conditions such as temperature, pressure, humidity, and inflow velocity makes it difficult to accurately reflect the multi-physics coupled response characteristics of internal combustion engines and their key components under complex service conditions. This is especially true for components highly sensitive to environmental conditions and inflow quality, such as the intake system, turbocharger, intercooler, cooling module, and engine compartment thermal management. The aforementioned separate testing methods struggle to accurately reveal the performance evolution under the combined effects of aerodynamic and environmental parameter changes, resulting in limitations in terms of operational condition reproducibility, data correlation, and engineering representativeness.

[0006] Therefore, existing technologies often employ a combination of wind tunnels and environmental chambers, interface coupling, or phased testing to achieve joint simulation of aerodynamic and environmental conditions. However, from the perspective of test system configuration and boundary condition control, this split-type "wind tunnel + environmental chamber" approach has inherent shortcomings: First, the wind field and environmental field belong to different controlled areas, making it difficult to achieve strictly co-domain loading; second, there are many connection interfaces between systems, resulting in complex structural integration and significant challenges in achieving sealing; third, airflow organization and temperature, pressure, and humidity control are prone to mutual interference, leading to insufficient stability of test boundary conditions; and fourth, the consistency, repeatability, and engineering comparability of test conditions are difficult to guarantee. Based on these problems, simply using the approach of splicing equipment is no longer sufficient to meet the needs of simulating highly complex service conditions, objectively driving the evolution of test systems from a split-combination model to an integrated platform model.

[0007] For aircraft components, actual service life involves more than just a single aerodynamic force or a single low-pressure, low-temperature environment. Instead, they are simultaneously subjected to the coupled effects of multiple factors, including incoming air loads, rarefied air effects, low-temperature environments, humidity variations, and even the risk of condensation, all within the same spatiotemporal conditions. This type of service condition is essentially a multi-physics-field combined action scenario. Existing single-type test equipment can only independently control environmental parameters such as wind speed or temperature, pressure, and humidity, making it difficult to synchronously, stably, and with high fidelity simulate these factors on a single platform. Therefore, it is insufficient to meet the realistic testing requirements under complex high-altitude conditions.

[0008] Furthermore, with the continuously increasing requirements for comprehensive environmental adaptability verification of UAV airfoil components, missile control surfaces, thermal protection structures, airborne sensors, and other functional components, the test evaluation system is gradually shifting from traditional single-factor performance assessment to comprehensive performance verification under multi-physics coupling conditions. The authenticity, synchronicity, and coupling of the test boundary conditions directly affect the engineering representativeness and application value of the test results. Summary of the Invention

[0009] (1) Purpose of the invention

[0010] The present invention discloses an in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components. The main motivation for the invention stems from a deep understanding of the need to reproduce test boundary conditions under real high-altitude service conditions. The present invention aims to overcome the technical limitations of existing wind tunnels and environmental chambers operating separately and being loaded in separate domains, and to construct a comprehensive test platform that can simultaneously form a controllable wind field and a high-altitude environmental field in the same enclosed space, so as to achieve high-fidelity reproduction and comprehensive verification of complex high-altitude service conditions.

[0011] To address the shortcomings and defects of existing technologies, the present invention provides an in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components. The technical problem to be solved is: to construct an in-cabin wind tunnel test platform that can simultaneously and stably establish an airflow field and a high-altitude environmental field in a closed high-altitude environment simulation chamber, thereby realistically reproducing the coupled working conditions that aircraft components endure under high-altitude comprehensive environments such as low air pressure, low temperature, and high humidity.

[0012] The present invention discloses an in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components. The core objective of the invention is to provide an in-cabin wind tunnel test platform system for high-altitude performance testing of aircraft components. By setting up a closed-loop wind tunnel entirely within a sealed high-altitude environment simulation chamber, and combining it with a high-altitude parameter adjustment system, a unidirectional isolation structure, an environmental homogenization structure, and a unified control system, a high-fidelity ground simulation of high-altitude aerodynamic-environment coupled operating conditions can be achieved. This solves the problems of existing technologies, such as separation of wind tunnel and environmental chamber, weak multi-parameter coordination capability, insufficient realism in operating condition reproduction, poor sealing reliability, and difficulty in ensuring the stability of the flow field in the test section.

[0013] Specifically, one of the objectives of the technical solution described in this invention is to provide an integrated platform that integrates the wind tunnel test system inside the high-altitude environment simulation chamber to form an integrated test platform.

[0014] Specifically, one of the objectives of the technical solution described in this invention is to provide co-domain coupling test conditions so that parameters such as wind speed, air pressure, temperature, and humidity can act together on the specimen in the same controlled space.

[0015] Specifically, one of the objectives of the technical solution described in this invention is to provide a closed-loop wind tunnel structure to achieve a closed-loop, controllable, and stable wind tunnel channel within the cabin;

[0016] Specifically, one of the objectives of the technical solution described in this invention is to provide a unified and coordinated control foundation, which provides a platform foundation for multi-parameter coordinated regulation through sensor arrangement, environmental adjustment interface, homogenization structure and control system;

[0017] Specifically, one of the objectives of the technical solution described in this invention is to improve sealing performance and engineering feasibility, reduce external long pipelines and inter-cabin interfaces, and improve cabin integrity and long-term operational reliability.

[0018] (2) Inventive concept

[0019] The present invention discloses an in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components. The main inventive concept is as follows: addressing the problem that existing wind tunnels and high-altitude environment simulation chambers are set up separately, and that it is difficult to stably establish wind fields and high-altitude environmental fields in the same controlled space, the present invention proposes an in-cabin wind tunnel test platform that sets up a closed-loop wind tunnel as a whole inside a sealed high-altitude environment simulation chamber. Through the coordinated configuration of a high-altitude parameter adjustment system, a unidirectional isolation structure, an in-cabin environment homogenization structure, a general sensor layout, and a unified control system, the target wind speed, air pressure, temperature, and humidity can act on the test piece in the same space, thereby achieving high-fidelity ground simulation of the high-altitude aerodynamic-environment coupling conditions of aircraft components.

[0020] First, one of the inventive concepts is the construction of a co-domain platform. The core task of this co-domain platform construction is to provide a unified spatial carrier for high-altitude dynamic-environment coupling experiments. Its corresponding structure includes a sealed high-altitude environment simulation chamber and a wind tunnel testing system housed within it. The mechanism for achieving this is to place the wind tunnel as a whole within the environment chamber, so that the airflow, temperature, pressure, and humidity environment experienced by the specimen are formed within the same sealed space, rather than being provided separately by separate devices. The result is the co-domain superposition of the wind field and the high-altitude environmental field, providing a foundation for subsequent integrated operating condition construction.

[0021] Second, one of the inventive concepts is the establishment of an environmental field. The core task of establishing an environmental field is to create a target high-altitude environment within the enclosed space. The corresponding structure for establishing an environmental field includes a temperature control module, a pressure control module, and a humidity control module. The mechanism for establishing an environmental field involves regulating the temperature, pressure, and humidity of the gas entering the chamber and then introducing the regulated gas into the environmental chamber; the result is the formation of a target temperature field, pressure field, and humidity field within the chamber.

[0022] Third, one of the inventive concepts is the establishment of a wind field. The core task of wind field establishment is to create a stable and controllable airflow field in the target high-altitude environment. The corresponding structure for wind field establishment includes a wind tunnel fan, a contraction section, a rectifier, a test section, and a return flow channel. The mechanism for wind field establishment is that the wind tunnel fan provides circulating power, the contraction section generates the required flow velocity, the rectifier improves the flow field quality, and the return flow channel forms a closed loop; the result is the establishment of stable aerodynamic loading conditions under cabin environmental conditions.

[0023] Fourth, one of the inventive concepts is isolation and stability assurance. The core task of isolation and stability assurance is to ensure that the established environmental field and wind field are not disturbed by external factors and remain stable. The corresponding structures for isolation and stability assurance include a one-way valve, environmental chamber insulation, and a closed-loop wind tunnel structure. The mechanism for achieving isolation and stability assurance is to prevent the gas inside the chamber from flowing back to the parameter regulation system through a one-way valve, to reduce heat exchange between the chamber and the outside environment through insulation, and to reduce external disturbances and additional pressure loss through a closed-loop wind tunnel; the result is improved stability in establishing and maintaining operating conditions.

[0024] Fifth, one of the inventive concepts is maintaining environmental consistency. The core task of maintaining environmental consistency is to reduce the differences in spatial distribution within the chamber and maintain the consistency of the boundary conditions of the environment surrounding the specimen. The corresponding structure for maintaining environmental consistency includes a temperature and humidity sensor array and an intelligent environmental homogenizing fan array. The mechanism for maintaining environmental consistency lies in the real-time sensing of environmental parameters at multiple points within the chamber by the temperature and humidity sensor array, and the active homogenizing of the local environment by the intelligent environmental homogenizing fan array based on the sensing results; the result is a reduction in local temperature and humidity gradients, thereby improving the consistency of the environment within the chamber.

[0025] Sixth, one of the inventive concepts is unified and coordinated control. The core task of unified and coordinated control is to uniformly schedule the establishment of the environment, the establishment of the wind field, the assurance of stability, and the maintenance of consistency. The corresponding structure of unified and coordinated control includes a two-way coupled environmental dynamic control system and related sensors. The implementation mechanism of unified and coordinated control lies in collecting cabin environmental parameters, wind tunnel state parameters, and feedback information from the execution unit, and coordinating the operation of the environmental regulation system, the wind tunnel system, and the homogenization device accordingly; the result is that the wind field and the environmental field can be collaboratively established and stably maintained under the target operating conditions on the same platform.

[0026] (3) Specific technical solutions

[0027] Overall, the in-cabin wind tunnel test platform system for high-altitude performance testing of aircraft components described in this invention consists of an environmental cabin body layer, an in-cabin wind tunnel layer, a parameter adjustment layer, and a closed-loop control layer. The in-cabin enclosed wind tunnel test system is installed as a whole inside the high-altitude environment simulation cabin and forms an integrated installation with the high-altitude environment simulation cabin.

[0028] The environmental cabin body layer, as the high-altitude environment matrix for dynamic homogenization, includes an environmental cabin body (22) and an environmental cabin body insulation layer (1) set on the outside of the environmental cabin body (22). It can construct and maintain a high-altitude background environment with low air pressure, low temperature and set humidity in a closed space. The intelligent environmental homogenization fan array 1 (3) and the intelligent environmental homogenization fan array 2 (16) are respectively installed in the upper and lower areas of the inner wall of the high-altitude environment simulation cabin, forming an upper and lower partitioned homogenization arrangement facing the overall background environment field inside the cabin. The environmental cabin body insulation layer (1) can suppress the heat exchange between the cabin and the outside under low temperature conditions, improve the stability maintenance capability of the low temperature background environment and reduce the environmental drift caused by the operation of the wind tunnel. It can also suppress the macroscopic temperature and humidity gradient caused by the operation of the built-in wind tunnel in the cabin through multi-point sensing and active homogenization mechanism, so that the test airflow circulates independently inside the closed high-altitude environment cabin and does not directly exchange with the outside, providing stable and consistent environmental boundary conditions for the test section (11).

[0029] The wind tunnel layer inside the cabin is a closed-loop, controllable wind tunnel test channel established inside the sealed high-altitude environment cabin, which can ensure the quality of the flow field. The wind tunnel fan (6), adjustable contraction section (7), rectifier (8) and test section (11) are connected in series along the airflow direction and together with the wind tunnel shell (24) form a closed-loop wind tunnel circuit set in the high-altitude environment simulation cabin, so that the test airflow forms an independent circulation in the cabin and does not directly exchange with the outside. The anti-condensation electric heating film (4) is attached to the outer wall of the wind tunnel shell (24) to provide local heating protection for the wind tunnel shell (24) and the adjacent area of ​​the test section (11). It can carry the measurement and control components in the test section (11) and realize wireless data transmission and power supply management. The test component (10) is installed inside the test section (11) through the fully built-in wireless measurement and control support rod (25). The operation of the wind tunnel fan (6), adjustable shrink section (7) compensation, composite rectification and anti-condensation protection maintains a stable, uniform and measurable test flow field under low pressure, low temperature and variable humidity conditions, providing the test piece (10) with local aerodynamic loading conditions in a real high-altitude environment; the test piece (10) is installed inside the test section (11) through a fully built-in wireless measurement and control support rod (25); the fully built-in wireless measurement and control support rod (25) is completely arranged inside the high-altitude environment simulation chamber and extends into the test section (11) to realize the installation support and attitude adjustment of the test piece (10) without wiring through the chamber and without setting external support components through the chamber; in addition, multiple sensors are set in the wind tunnel layer inside the chamber, which work together with the wind tunnel fan (6), adjustable shrink section (7), rectifier (8) and test section (11) to ensure the operation of the wind tunnel test chamber;

[0030] The parameter adjustment layer, consisting of a temperature control module (18), a pressure control module (19), a humidity control module (20), an external clean gas input interface (28), and one-way valves (17 and 21) located between the parameter adjustment layer and the high-altitude environment simulation chamber, constitutes a background parameter supply and dynamic maintenance subsystem for high-altitude environment-wind tunnel coupled test conditions. The temperature and humidity sensor array (2) is fixedly installed in multiple spatial locations inside the high-altitude environment simulation chamber, at least at multiple installation points in the upper, lower, and adjacent areas of the test section (11) of the chamber, which can characterize the spatial stratification and gradient of temperature and humidity inside the chamber and obtain spatial distribution information of temperature and humidity parameters inside the chamber. The high-altitude parameter preprocessing unit includes an external gas input interface and a temperature control module (18) arranged in series along the external gas flow direction. The pressure control module (19) and humidity control module (20) pre-process external gas in the order of temperature-pressure-humidity before inputting it into the sealed high-altitude environment chamber. One-way valves (17) and (21) are set on the gas exchange path between the parameter adjustment layer and the high-altitude environment simulation chamber. They can restrict the backflow and return of gas in the chamber to the parameter adjustment layer along the parameter adjustment path. Under the disturbance conditions of the closed-loop wind tunnel operation in the chamber, the parameter supply side and the test load side are isolated at the boundary. The parameter adjustment layer performs temperature, pressure and humidity pre-processing on the gas entering the high-altitude environment simulation chamber. Combined with one-way isolation and pre-balancing and slow stop operation management, the target high-altitude background parameters are continuously established, input and maintained under the disturbance conditions of the wind tunnel operation in the chamber.

[0031] The closed-loop control layer mainly consists of an industrial computer (23), a data acquisition card (31), a UWB wireless communication interface (29), and a control interface (30) for connecting with the wind tunnel system, parameter adjustment system, environmental homogenization components, and anti-condensation unit. As the integrated operation center of the environmental cabin body layer, the cabin wind tunnel layer, and the parameter adjustment layer, the closed-loop control layer implements cross-physical field linkage control of the wind tunnel system, the high-altitude parameter adjustment system, the environmental homogenization structure, and the anti-condensation unit. It performs coupled and coordinated control of the establishment and maintenance of the high-altitude background environment, the loading of local test airflow and the maintenance of flow field quality, and the supply and compensation of temperature, pressure, and humidity in the same time and space.

[0032] Environmental chamber body layer for in-cabin wind tunnel testing system

[0033] Furthermore, the environmental cabin body layer is composed of a high-altitude environment simulation cabin and an internal environment homogenization component; the high-altitude environment simulation cabin includes an environmental cabin body (22) and an environmental cabin body insulation layer (1) disposed on the outside of the environmental cabin body (22), which is used to construct and maintain a high-altitude background environment with low air pressure, low temperature and set humidity in a closed space; the environmental cabin body insulation layer (1) can suppress the heat exchange between the cabin and the outside under low temperature conditions, improve the stability maintenance capability of the low temperature background environment and reduce the environmental drift caused by wind tunnel operation;

[0034] The cabin environment homogenization component includes a temperature and humidity sensor array (2) and intelligent environment homogenization fan array 1 (3) and intelligent environment homogenization fan array 2 (16) arranged symmetrically inside the cabin body (22); the temperature and humidity sensor array (2) is used to acquire temperature and humidity data of multiple spatial locations inside the cabin body (22) in real time and calculate spatial temperature difference and humidity difference; the intelligent environment homogenization fan array 1 (3) or intelligent environment homogenization fan array 2 (16) performs start-stop or speed adjustment based on the comparison result of the spatial temperature difference and humidity difference with the preset threshold, and can actively suppress the macroscopic temperature and humidity gradient inside the cabin under the conditions of heat release, flow disturbance and humidity migration caused by the operation of the closed circulating wind tunnel inside the cabin.

[0035] The wind tunnel layer located inside the sealed high-altitude environment simulation chamber

[0036] Furthermore, the wind tunnel layer inside the cabin mainly consists of a wind tunnel fan (6), a contraction section (7), a rectifier (8), a test section (11), and a wind tunnel shell (24) surrounding the contraction section (7), the rectifier (8), and the test section (11). The wind tunnel fan (6) is integrally built into the high-altitude environment simulation cabin and is connected to the contraction section (7), the rectifier (8), and the test section (11) to form a closed-loop air path, so that the test airflow does not directly exchange with the outside, and so that the wind tunnel layer inside the cabin does not damage the overall stability of the low-pressure, low-temperature, and humidity background environment inside the high-altitude environment simulation cabin when applying local airflow loads as an embedded circulating subsystem. The wind tunnel layer inside the cabin also includes The wind tunnel wind speed sensor (9) is installed in the test section (11) to measure the wind speed in the test section and to perform closed-loop correction on the wind tunnel fan (6). The wind tunnel fan (6) and the contraction section (7) are a dual actuator cooperative compensation structure. The contraction section (7) is used to adjust the rotation speed in conjunction with the wind tunnel fan (6). It can maintain the target wind speed and flow field stability of the test section (11) under the condition that the gas density is reduced due to low air pressure. The rectifier (8) is a composite rectification structure. It can suppress turbulence and improve the flow velocity uniformity under low pressure, low temperature and variable humidity background conditions, thereby providing stable, uniform and measurable local aerodynamic loading conditions for the specimen.

[0037] Specifically, the wind tunnel layer inside the cabin, as an embedded circulation subsystem, does not disrupt the overall stability of the low-pressure, low-temperature, and humidity background environment inside the high-altitude environment simulation cabin when local airflow loads are applied; the sensors installed inside the wind tunnel layer include a wind tunnel wind speed sensor (9), which is installed on the test section (11) and can measure the wind speed of the test section (11) and perform closed-loop correction on the wind tunnel fan (6); the wind tunnel fan (6) and the adjustable contraction section (7) form a dual-actuator collaborative compensation structure, and the speed of the adjustable contraction section (7) and the wind tunnel fan (6) are linked and adjusted, which can maintain the target wind speed and flow field stability of the test section (11) under the condition that the gas density is reduced due to low air pressure; the rectifier 1 (8) and the rectifier 2 (12) are a composite rectification structure that together suppresses turbulence and improves the flow velocity uniformity under low pressure, low temperature and variable humidity background conditions, providing stable, uniform and measurable local aerodynamic loading conditions for the test object (10).

[0038] Specifically, the wind tunnel layer inside the cabin is also equipped with a wind tunnel wall temperature sensor (5), a wind tunnel gas temperature sensor (13), a wind tunnel humidity sensor (14), and a wind tunnel pressure sensor (15). When the wind tunnel inside the cabin is started, multiple sensors work together to monitor the wall temperature of the wind tunnel shell (24), the wind tunnel gas state parameters, and the drift of the operating conditions, which can support wind speed closed-loop correction and anti-condensation linkage control.

[0039] Specifically, the temperature and humidity sensor array (2) is a multi-point distributed sensor array, including at least multiple sampling points located in the upper, lower and test sections (11) and can identify the stratification of the cabin environment and local temperature and humidity drift. When starting, stopping or speed adjustment is performed, the temperature difference or humidity difference between any two sampling points of the temperature and humidity sensor array (2) exceeds the preset threshold as the trigger condition, so as to dynamically reduce and reorganize the macro temperature and humidity gradient in the cabin.

[0040] Specifically, the intelligent environment homogenizing fan array 1 (3) and the intelligent environment homogenizing fan array 2 (16) are non-continuously open fan arrays that start and stop and adjust speed according to thresholds, so as to reduce additional disturbances to the wind tunnel test flow field inside the cabin and reduce energy consumption; the intelligent environment homogenizing fan array 1 (3) and the intelligent environment homogenizing fan array 2 (16) are arranged in vertical partitions along the height direction of the environmental cabin body (22) or symmetrically arranged relative to the center of the cabin body, forming a layered homogenizing flow field organization facing the layering of the cabin environment.

[0041] Parameter adjustment layer for high-altitude environment-wind tunnel coupled testing

[0042] Furthermore, the parameter adjustment layer mainly consists of a temperature control module (18), a pressure control module (19), a humidity control module (20), an external clean gas input interface (28), and a one-way valve (17) and a one-way valve (21) set between the parameter adjustment layer and the high-altitude environment simulation chamber. The temperature control module (18), the pressure control module (19), and the humidity control module (20) work together on the same adjustment platform and jointly output the target temperature, pressure, and humidity parameters. The temperature control module (18), the pressure control module (19), and the humidity control module (20) work together to form an integrated "temperature-pressure-humidity" pretreatment unit, which can coordinate the temperature, pressure, and humidity of the working medium entering through the external clean gas input interface (28) before entering the high-altitude environment simulation chamber. The working medium immediately reaches the target low pressure, low temperature, and set humidity state before entering the chamber, and at the same time establishes and continuously maintains the target high-altitude background parameters in the chamber.

[0043] The temperature control module (18), pressure control module (19) and humidity control module (20) are connected in series along the flow direction of the external clean gas. The external clean gas input interface (28) is connected to the integrated pretreatment unit of "temperature-pressure-humidity" to provide the high-altitude environment simulation chamber with clean gas that has been pretreated by temperature, pressure and humidity.

[0044] Specifically, in the parameter adjustment layer, one-way valves (17) and (21) are set on the gas exchange path between the parameter adjustment layer and the high-altitude environment simulation chamber, which can restrict the backflow and return of gas in the chamber to the parameter adjustment layer along the parameter adjustment path, and implement boundary isolation between the parameter supply side and the test load side under the disturbance conditions of the closed-loop wind tunnel operation in the chamber.

[0045] Closed-loop control layer for high-altitude environment-aerodynamic load coupling tests

[0046] Furthermore, the closed-loop control layer mainly consists of an industrial computer (23), a data acquisition card (31), a UWB wireless communication interface (29), and a control interface (30) for connecting with the wind tunnel system, parameter adjustment system, environmental homogenization component, and anti-condensation unit. The industrial computer (23) accesses multi-source sensor feedback signals through the data acquisition card (31) or the UWB wireless communication interface (29). The multi-source sensor feedback signals include at least the wind speed signal from the wind tunnel wind speed sensor (9), the pressure signal from the wind tunnel pressure sensor (15), the spatial temperature and humidity distribution signal from the temperature and humidity sensor array (2), and the wall temperature signal from the wind tunnel wall temperature sensor (5). The industrial computer (23) controls the wind tunnel based on the multi-source sensor feedback signals. The tunnel ventilation fan (6) and the contraction section (7) servo mechanism, temperature control module (18), pressure control module (19), humidity control module (20), intelligent environmental homogenizing fan array 1 (3), intelligent environmental homogenizing fan array 2 (16) and anti-condensation electric heating film (4) implement cross-physical field linkage control. Under the continuous operation disturbance of the wind tunnel in the cabin, they work together to maintain the target high-altitude background environmental parameters and the flow field stability of the test section, and perform time-series management of the entire process of pre-balancing, steady-state operation and slow stop reset. The industrial computer (23) incorporates wind speed, pressure, temperature and humidity spatial distribution and wall temperature as coupling variables into a unified discrimination and unified adjustment framework to avoid mutual disturbance amplification caused by independent closed-loop control of temperature, pressure, humidity and wind speed.

[0047] Secondly, in terms of operation, the in-cabin wind tunnel test platform system for high-altitude performance testing of aircraft components described in this invention is configured with a pre-balance control strategy and a slow-stop control strategy in the parameter adjustment layer.

[0048] The pre-balance control strategy requires the environment to be established before the wind tunnel is started during the pre-balance stage. The parameter adjustment layer is configured with the pre-balance control strategy to adjust the air pressure, temperature and humidity in the chamber to the target value and maintain it stably for a preset time before starting the wind tunnel system in the chamber, so as to avoid the wind tunnel operation disturbance from interfering with the environment establishment stage.

[0049] The slow-stop control strategy requires unloading the airflow before withdrawing the environment during the slow-stop phase. The parameter adjustment layer is configured with a slow-stop control strategy. At the end of the test, the airflow loading in the cabin wind tunnel is reduced and closed first, and then the temperature control module (18), pressure control module (19) and humidity control module (20) are delayed and closed to reduce the risk of pressure fluctuation, temperature and humidity drift and condensation caused by the shutdown transient.

[0050] Thirdly, in terms of operation, the in-cabin wind tunnel test platform system for high-altitude performance testing of aircraft components described in this invention has an industrial computer (23) with background field spatial consistency control and "pre-balance-steady-stop" timing control;

[0051] The industrial computer (23) takes the spatial consistency of the background environment field inside the cabin as an independent controlled target and calculates the temperature difference or humidity difference between any two sampling points based on the temperature and humidity sensor array (2). When the temperature difference or humidity difference exceeds the preset threshold, the intelligent environmental homogenization fan array is triggered to start, stop or adjust speed through the control interface (30) to actively reduce the macro temperature and humidity gradient inside the cabin.

[0052] The industrial computer (23) performs full-process timing control of pre-balancing, steady-state operation and slow stop reset. In the pre-balancing stage, the industrial computer (23) first controls the temperature control module (18), pressure control module (19) and humidity control module (20) to make the cabin environment reach and stabilize the target value before starting the cabin wind tunnel. In the slow stop reset stage, the industrial computer (23) first reduces and releases the wind tunnel airflow load and then delays the removal of temperature, pressure and humidity regulation to reduce the risk of transient disturbances during start-up and shutdown, temperature and humidity drift and condensation.

[0053] Fourth, in terms of connection method, the in-cabin wind tunnel test platform system for high-altitude performance testing of aircraft components described in this invention has overall mechanical-installation connection, fluid connection and electrical signal connection.

[0054] Integral mechanical-installation connection method of the in-cabin wind tunnel test platform-level system

[0055] Furthermore, the overall mechanical-installation connection method of the cabin wind tunnel test platform system is as follows: the cabin closed wind tunnel test system is set up as a whole inside the high-altitude environment simulation chamber and integrated with the high-altitude environment simulation chamber; the wind tunnel fan (6), the contraction section (7), the rectifier (8) and the test section (11) are mechanically connected in sequence along the airflow direction, installed in series and together with the wind tunnel shell (24) to form a closed loop wind tunnel set in the high-altitude environment simulation chamber, so that the test airflow forms an independent circulation in the chamber and does not directly exchange with the outside; the cabin closed wind tunnel test system includes the wind tunnel shell (24), and the anti-condensation electric heating film (4) is attached to the outer wall of the wind tunnel shell (24) to implement local heating protection for the wind tunnel shell and the adjacent area of ​​the test section (11); the intelligent environment homogenization fan array 1 (3) and the intelligent ring The ambient temperature equalization fan array 2 (16) is installed in the upper and lower regions of the inner wall of the high-altitude environment simulation chamber, forming an upper and lower partitioned equalization arrangement facing the overall background environment field inside the chamber; the temperature and humidity sensor array (2) is fixedly installed in multiple spatial positions inside the high-altitude environment simulation chamber, at least in multiple installation points in the upper, lower and adjacent areas of the test section (11) inside the chamber, which can characterize the spatial stratification and gradient of temperature and humidity inside the chamber and obtain the spatial distribution information of temperature and humidity parameters inside the chamber; the test piece (10) is installed inside the test section (11) through the fully built-in wireless measurement and control support rod (25); the fully built-in wireless measurement and control support rod (25) is completely arranged inside the high-altitude environment simulation chamber and extends into the test section (11) to realize the installation support and attitude adjustment of the test piece (10) without wiring through the chamber and without setting external support components through the chamber.

[0056] Fluid connection method of in-cabin wind tunnel test platform-level system

[0057] Furthermore, the fluid connection method of the in-cabin wind tunnel test platform system is as follows: the system fluid path forms a hierarchical connection relationship of "external air source pretreatment - environmental chamber background establishment - in-cabin wind tunnel closed circulation"; external clean gas enters the high-altitude parameter adjustment system through the external clean gas input interface (28), and sequentially passes through the temperature control module (18), pressure control module (19) and humidity control module (20) along the flow direction to perform coordinated pretreatment of temperature, pressure and humidity on the working medium, so that the working medium reaches the preset high-altitude environmental parameter state before entering the high-altitude environment simulation chamber; the pretreated working medium passes through the high-altitude parameter adjustment system and the high-altitude environment One-way valve (17) between the simulation chambers enters the interior of the high-altitude environment simulation chamber to establish a background environment with target temperature, target pressure and target humidity in the high-altitude environment simulation chamber; the closed wind tunnel test system is set inside the high-altitude environment simulation chamber and forms an independent closed circulating airflow loop in the background environment, so that the working medium in the wind tunnel loop continues to circulate under the temperature, pressure and humidity conditions in the chamber and does not directly exchange with the outside; the one-way valve (21) set between the high-altitude parameter adjustment system and the high-altitude environment simulation chamber can restrict the reverse flow of gas in the environment chamber to the high-altitude parameter adjustment system, and suppress the backflow interference caused by the low pressure and internal circulation conditions in the chamber to the parameter adjustment side.

[0058] Electrical signal connection method of the in-cabin wind tunnel test platform-level system

[0059] Furthermore, the electrical signal connection method of the cabin wind tunnel test platform-level system is as follows: each functional unit forms a unified monitoring-control network in terms of electrical connection and signal transmission, and the industrial computer (23) serves as the core control node of the bidirectional coupled environmental dynamic control system; the data acquisition interface is simultaneously connected to the temperature and humidity sensor array, including at least the wind tunnel pressure sensor (15), the wind tunnel wind speed sensor (9), and the wind tunnel wall temperature sensor (5), so that the industrial computer (23) can obtain multi-source feedback quantities characterizing the high-altitude background environment, the flow field of the test section, and the thermal state of the wind tunnel wall; the control interface (30) is at least simultaneously connected to the wind tunnel fan (6), the contraction section servo mechanism, and the temperature control module (18), the pressure control module (19), and the humidity control module (20) to realize the linkage adjustment of the wind speed establishment of the test section and the temperature, pressure, and humidity background establishment in the cabin within the same control framework; the industrial computer (23) establishes an electrical connection with the temperature and humidity sensor array, and can obtain the temperature, humidity, and air pressure in the high-altitude environment simulation cabin in real time. The status signals of wind speed and wind tunnel shell wall temperature in the test section; the control interface (30) is further connected to the homogenizing fan array (3, 16) and the electric heating film (4) so ​​that the industrial computer (23) can simultaneously realize the uniformity adjustment of temperature and humidity space in the cabin and the anti-condensation protection of the wind tunnel shell in the same monitoring-control network; the industrial computer (23) is electrically connected to the wind tunnel fan (6), the contraction section servo mechanism, the temperature control module (18), the pressure control module (19), the humidity control module (20), the electric heating film (4) and the homogenizing fan array (3, 16), and implements linkage adjustment of each execution unit based on the status signals to realize unified control of wind speed maintenance, environmental parameter establishment, background field homogenization and anti-condensation protection; the fully built-in wireless measurement and control support rod (25) set inside the test section (11) interacts with the industrial computer (23) through the UWB wireless communication protocol to exchange measurement data and control commands, so that the attitude adjustment signal and measurement data of the test piece (10) do not need to be transmitted through the cabin cable.

[0060] Fifth, regarding the coupling links, the in-cabin wind tunnel test platform system for high-altitude performance testing of aircraft components described in this invention has an environmental establishment coupling link, a cabin sealing and measurement coupling link, and a "pre-balance-steady-state control-gradual stop" coupling link.

[0061] Establishing an environmental coupling link for the in-cabin wind tunnel test platform-level system

[0062] Furthermore, the environmental coupling link of the in-cabin wind tunnel test platform system includes a high-altitude parameter adjustment unit composed of a temperature control module (18), a pressure control module (19), and a humidity control module (20), which is used to implement integrated adjustment of temperature, pressure, and humidity of the working medium entering the system; the adjusted working medium is input into the high-altitude environment simulation chamber through a one-way valve to provide the chamber with an environmental medium that meets the target working conditions; the high-altitude environment simulation chamber includes an environment chamber body (22) and an environment chamber body insulation layer (1), wherein the environment chamber body (22) forms a dense The enclosed space is used to contain the environmental medium. The thermal insulation layer (1) of the environmental chamber is used to reduce the heat exchange between the inside and outside of the chamber to maintain the stability of the temperature, pressure and humidity boundaries inside the chamber. The temperature and humidity sensor array (2) inside the chamber performs multi-point real-time detection of the temperature and humidity status at different locations inside the chamber to obtain spatial distribution information. Furthermore, when the temperature and humidity sensor array detects that the temperature or humidity deviation in any area exceeds the preset threshold, the intelligent environmental homogenizing fan array 1 (3) and the intelligent environmental homogenizing fan array 2 (16) operate under the scheduling of the control system to actively reduce and homogenize the macroscopic temperature and humidity gradient inside the chamber.

[0063] Cabin sealing and measurement coupling link of the in-cabin wind tunnel test platform system

[0064] Furthermore, the cabin sealing and measurement coupling link of the cabin wind tunnel test platform system is as follows: the test piece (10) is set inside the test section (11) and mechanically supported by a fully built-in wireless measurement and control support rod (25); the fully built-in wireless measurement and control support rod (25) is set inside the high-altitude environment simulation cabin and located inside the test section (11) to perform attitude adjustment and aerodynamic response measurement of the test piece (10); the fully built-in wireless measurement and control support rod (25) integrates a six-dimensional force measurement unit (26) to acquire lift, drag, lateral force and torque signals; the fully built-in wireless measurement and control support rod (25) and the external The control system interacts with data and control commands through a wireless communication protocol, so that attitude adjustment signals and measurement data do not need to be transmitted through the cabin cable, thereby reducing the number of cabin penetration interfaces and reducing the risk of leakage under low pressure conditions; the UWB wireless communication protocol realizes the return of measurement data and the issuance of attitude adjustment commands through the UWB wireless communication interface (29); in addition, the high-altitude environment simulation cabin works together with the closed wind tunnel circuit inside the cabin through the isolation structure of one-way valve 1 (17) or one-way valve (21) to perform high-precision measurement of the attitude and aerodynamic response of the specimen under the premise of maintaining the sealed boundary conditions.

[0065] The pre-balancing-steady-state control-deceleration coupling link of the in-cabin wind tunnel test platform-level system

[0066] Furthermore, the "pre-balancing-steady-state control-gradual shutdown" coupling link of the in-cabin wind tunnel test platform-level system is as follows: the test operation process is executed sequentially in the pre-balancing phase, steady-state control phase, and gradual shutdown phase;

[0067] During the pre-balancing phase, the high-altitude parameter adjustment system first establishes and adjusts the temperature, pressure and humidity inside the high-altitude environment simulation chamber, so that the environmental parameters inside the chamber reach the preset target value and remain stable for a predetermined time, while the wind tunnel system inside the chamber remains in an unactivated state.

[0068] During the steady-state control phase, the wind tunnel system inside the cabin is started and operated. The control system implements synchronous closed-loop adjustment of environmental parameters, wind speed in the test section, uniformity of the cabin environment, and anti-condensation status, so that the background environmental field, local test flow field and anti-condensation protection are coordinated and maintained stably under the same operating conditions.

[0069] During the slow-down phase, the wind tunnel fan is first decelerated to gradually release the test airflow load, and then the high-altitude parameter adjustment system is shut down after a delay to reduce the risk of sudden pressure changes, temperature and humidity drift and local condensation caused by the shutdown transient.

[0070] Overall airflow path of the in-cabin wind tunnel test platform-level system

[0071] Furthermore, the overall air path of the cabin wind tunnel test platform system includes an external air path located outside the high-altitude environment simulation cabin (22) and an internal air path located inside the high-altitude environment simulation cabin (22);

[0072] The inlet path of the external gas path is: external clean gas input interface (28) → temperature control module (18) or pressure control module (19) or humidity control module (20) → one-way valve 1 (17) → high-altitude environment simulation chamber (22);

[0073] The external gas path can establish and maintain the target high-altitude background environment inside the high-altitude environment simulation chamber (22); the external gas path includes at least an external clean gas input interface (28), a temperature control module (18), a pressure control module (19), a humidity control module (20), a one-way valve 1 (17), and the high-altitude environment simulation chamber (22); the temperature control module (18) is used to adjust the temperature of the input gas, the pressure control module (19) can adjust the pressure of the input gas, the humidity control module (20) can adjust the humidity of the input gas, and the one-way valve 1 (17) can suppress the backflow of gas in the environment chamber to the upstream adjustment module;

[0074] The external gas path also includes an outlet end or a recovery end. The high-altitude environment simulation chamber (22) is connected to the outlet end or recovery end via a one-way valve 2 (21) to form a gas discharge, chamber pressure recovery or working fluid replacement path. The one-way valve 2 (21) is set on the outlet side of the external gas path to ensure that the gas in the environment chamber is discharged or recovered in a predetermined direction and to prevent external backflow from disturbing the target working conditions in the environment chamber.

[0075] The flow path of the internal air passage is: cabin air → wind tunnel fan (6) → adjustable contraction section (7) → front rectifier 1 (8) → test section (11) → rear rectifier 2 (12) → wind tunnel outlet → cabin recirculation area → back to the inlet of wind tunnel fan (6).

[0076] The internal air path can establish the target test airflow of the test section (11) under the target high-altitude background environment; the internal air path is a closed-loop wind tunnel air path set inside the high-altitude environment simulation chamber (22), including at least a wind tunnel fan (6), an adjustable contraction section (7), a pre-rectifier (8), a test section (11), a post-rectifier (12), a wind tunnel shell (24), and an in-chamber recirculation zone; the wind tunnel shell (24) defines the boundary of the main channel, the wind tunnel fan (6) is used to provide circulation power, the adjustable contraction section (7) is used to improve the local acceleration capability, and the pre-rectifier 1 (8) and the post-rectifier (12) are respectively used to improve the inlet flow quality of the test section (11) and to regulate the downstream discharge flow of the test section (11).

[0077] Specifically, the external and internal air paths operate in the same high-altitude environment simulation chamber (22), so that the external air path determines the environmental parameters inside the chamber, and the internal air path determines the flow field parameters of the test section (11), thus realizing the coupled simulation of high-altitude environment and aerodynamic loading. The low-pressure, low-temperature and variable humidity background environment established by the external air path determines the density, dew point temperature and thermal and humid state of the gas in the internal air path, thereby affecting the ability to establish the target wind speed, the stability of the circulating flow field and the risk of condensation or frost on the wall in the test section (11). The circulating airflow in the internal air path affects the local wall temperature and local humid air state inside the chamber through convective heat transfer, local pressure distribution changes and flow field disturbances, thereby affecting the risk of condensation or frost.

[0078] Specifically, the overall air path of the in-cabin wind tunnel test platform system also includes a controller (23), which is connected to the temperature control module (18), pressure control module (19) and humidity control module (20) of the external air path, as well as the wind tunnel fan (6) and adjustable contraction section (7) of the internal air path. The controller (23) coordinates the control of the external air path and the internal air path based on the pressure, temperature, humidity, representative wind speed of the test section (11) and wall temperature in the environmental chamber, so that the external air path is responsible for establishing the target high-altitude background environment, and the internal air path is responsible for establishing the target test flow under the target high-altitude background environment, and for suppressing the risk of condensation or frost on the wall.

[0079] An in-cabin wind tunnel testing method for high-altitude aerodynamic coupling testing of aircraft components

[0080] Furthermore, the in-cabin wind tunnel testing method for high-altitude aerodynamic coupling testing of aircraft components described in this invention is applied to an in-cabin closed-loop wind tunnel testing system within a sealed high-altitude environment simulation cabin, and includes the following steps:

[0081] S1. Set target operating conditions: Input the target wind speed, air pressure, temperature and relative humidity through the human-machine interface as the basis for subsequent control;

[0082] S2. Environmental pre-equilibration: Before the test begins, environmental pre-equilibration is performed. Gas that has been conditioned for temperature, pressure and humidity is introduced into the environmental chamber through the high-altitude parameter adjustment system. The environmental parameters inside the chamber are adjusted to the target values ​​and stabilized for 10-30 minutes, so that the air pressure, temperature and humidity inside the environmental chamber reach the target working conditions.

[0083] S3. Start the micro wind tunnel device and execute bidirectional coupling control: Start the wind tunnel layer inside the cabin and execute bidirectional coupling control. Adjust the speed of the wind tunnel fan (6) or the effective cross-sectional area of ​​the throat of the adjustable contraction section (7) according to the deviation between the actual wind speed and the target wind speed in the test section (11) to establish and maintain the target wind speed in the test section (11). At the same time, control the operation of the environmental homogenization fan array 1 (3) and the intelligent environmental homogenization fan array 2 (16) according to the uniformity of the cabin environment, and control the operation of the anti-condensation heating device according to the relationship between the wall temperature and the dew point temperature of the cabin air.

[0084] S4. Real-time data acquisition: Real-time monitoring of cabin air pressure, temperature, relative humidity, wind tunnel gas state parameters, and wind tunnel shell wall temperature through various sensors installed inside the cabin, and collection of necessary feedback information;

[0085] S5. Model testing: Under stable working conditions, the fully built-in wireless measurement and control support rod (25) completes the model angle of attack adjustment, and transmits the data of the six-dimensional force measurement unit (26) back to the computer (23) through the UWB wireless communication interface (29) to achieve high-precision measurement without cabin penetration;

[0086] S6. Slow Stop and Reset: After the test, slow stop and reset are performed. First, gradually reduce the speed of the wind tunnel fan (6) to zero. After a delay of 2 minutes, shut down the high-altitude parameter adjustment system, and then shut down the environmental parameter control unit and auxiliary equipment to avoid pressure fluctuations or condensation problems in the cabin due to sudden shutdown.

[0087] Specifically, in the S2. environmental pre-balancing process, the high-altitude parameter adjustment system includes a temperature control module (18); a pressure control module (19); and a humidity control module (20). The high-altitude parameter adjustment system is connected to the environmental chamber via a one-way valve 1 (17) or a one-way valve (21) to establish the target high-altitude background environment in the environmental chamber. In the environmental pre-balancing stage, the wind tunnel fan (6) is kept closed to avoid airflow disturbance affecting the establishment of the environment.

[0088] Once the air pressure, temperature, and humidity inside the environmental chamber reach the target operating conditions and remain stable for a preset time, proceed to the next step (S3. Start the wind tunnel and execute bidirectional coupling control), with a preset time of 10 to 30 minutes.

[0089] Specifically, in S3. activating the wind tunnel and executing bidirectional coupling control, the uniformity of the environmental space inside the cabin is monitored by the cabin temperature and humidity sensor array. When the temperature difference between any two points inside the environmental cabin exceeds ±1℃ and the humidity difference exceeds ±5%RH, the intelligent environmental homogenization fan array is activated to improve the uniformity of the cabin environment.

[0090] The dew point temperature is calculated based on the temperature, humidity and pressure of the gas inside the chamber, and the dew point temperature is compared with the temperature of the wind tunnel shell wall. When the wall temperature is lower than the dew point temperature or lower than the dew point temperature plus a preset safety margin, the anti-condensation electric heating film (4) is automatically activated to locally heat the easily condensable areas of the wind tunnel shell (24) and the outer wall of the test section (11).

[0091] (4) Inventive principle

[0092] The present invention describes an in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components. The main working principle is as follows: a closed high-altitude environment simulation chamber is used as the external controlled space. A closed-loop wind tunnel test system is set up inside the controlled space so that the test specimen is placed in the airflow field and high-altitude environment field formed in the same closed space. The target temperature, pressure and humidity environment is established in the closed high-altitude environment simulation chamber using the high-altitude parameter adjustment system. In this environment, a closed-loop wind tunnel is formed by the wind tunnel fan (6), adjustable contraction section (7), rectifier 1 (8) and rectifier 2 (12), test section (11) and return channel to form a stable and controllable airflow path. The high-altitude parameter regulation system is used to regulate the temperature, pressure, and humidity of the gas entering the environmental chamber, thereby establishing a target high-altitude environment within the chamber. The wind tunnel testing system is used to form a stable and controllable circulating airflow under the environmental conditions to apply aerodynamic loads to the specimen. The one-way valve is used to prevent the gas inside the chamber from flowing back to the parameter regulation system, and the insulation is used to reduce heat exchange between the chamber and the outside environment. The temperature and humidity sensor array is used to acquire the distribution of environmental parameters at different locations inside the chamber, and the intelligent environmental homogenizing fan array is used to actively homogenize the local environment inside the chamber based on the distribution information. The bidirectional coupled environmental dynamic control system uniformly schedules each execution unit based on the environmental parameters inside the chamber and the wind tunnel state parameters, thereby simultaneously establishing and maintaining the airflow field and high-altitude environmental field required by the specimen in the same sealed space, realizing the coordinated establishment and stable maintenance of wind speed, air pressure, temperature, and humidity on the same platform.

[0093] The present invention describes an in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components. The specific working principle can be divided into the construction of the same-domain platform, the establishment of the environmental field, the establishment of the wind field, isolation and stability assurance, environmental consistency maintenance, and unified collaborative control.

[0094] Firstly, the in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components described in this invention are based on the principle of co-domain construction: a high-altitude environment simulation cabin provides a sealed and controlled space, and the entire wind tunnel is set up inside this space. Therefore, the airflow, temperature, pressure, and humidity environment experienced by the test specimens come from the same space, fundamentally avoiding the separation of operating conditions caused by the separation of the external wind tunnel and the internal environment.

[0095] Secondly, the wind tunnel test platform system and method for high-altitude performance testing of aircraft components described in this invention establishes the wind field by means of a closed loop consisting of a fan, a contraction section, a rectifier, a test section, and a return channel. The closed loop controls the airflow path and reduces pressure loss and external disturbances, thus enabling the formation of stable aerodynamic loading under cabin environmental conditions.

[0096] Thirdly, the in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components described in this invention establishes the environment by means of: a temperature control module, a pressure control module, and a humidity control module pre-treating the gas entering the cabin; the regulated gas then enters the sealed environment chamber, thereby establishing the target high-altitude environment field within the chamber.

[0097] Fourth, the in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components described in this invention has the following isolation and stabilization principles: a one-way valve prevents the gas inside the cabin from flowing back to the parameter adjustment system, insulation reduces heat exchange between the cabin and the outside world, and a closed-loop wind tunnel reduces external disturbances and additional pressure loss; therefore, the establishment and maintenance of the environmental field and wind field have better stability.

[0098] Fifth, the cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components described in this invention features unified and coordinated control as follows: a temperature and humidity sensor array perceives the environmental distribution at multiple points within the cabin in real time; an intelligent environmental homogenizing fan array actively adjusts the airflow organization based on the distribution information, thereby reducing the local temperature and humidity gradient within the cabin and maintaining the consistency of the environmental boundary conditions around the test specimen.

[0099] Sixth, the in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components described in this invention maintains consistency by means of the following principle: the control system collects in-cabin environmental parameters, wind tunnel state parameters and related feedback information; and coordinates the environmental conditioning system, wind tunnel system, homogenization device and other components according to the target operating conditions; thereby enabling the establishment of the environmental field, wind field, stability maintenance and consistency maintenance to no longer be separated from each other, but to operate in coordination, and ultimately jointly maintain the target high-altitude coupled operating conditions.

[0100] (5) Effects of the invention

[0101] The present invention discloses an in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components. It can simultaneously establish wind speed, air pressure, temperature and humidity conditions in the same sealed space, reduce pressure loss, heat loss and environmental disturbance introduced by external pipelines and cabin interfaces, and improve the stability, uniformity and sealing reliability of the flow field in the test section and the cabin environment, thereby providing a high-fidelity and highly repeatable high-altitude comprehensive performance test platform for aircraft components.

[0102] Firstly, the technical solution described in this invention, by setting the entire wind tunnel inside a high-altitude environment simulation chamber and forming a closed-loop air duct within the chamber, achieves the coupling of the wind field and the high-altitude environmental field within the same controlled domain. This allows the test specimen to be tested simultaneously under set wind speed, set air pressure, set temperature, and set humidity conditions. Therefore, the in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components described in this invention can effectively improve the realistic reproduction capability of high-altitude comprehensive operating conditions of aircraft components, enhance the co-locality, synchronicity, and consistency of test boundary conditions, and provide a more realistic and reliable test platform for high-altitude performance evaluation.

[0103] Secondly, the technical solution described in this invention, by employing an in-cabin closed-loop wind tunnel structure, avoids pipeline pressure loss, heat loss, humidity fluctuations, and external interference caused by external airflow. This improves the stability and repeatability of boundary condition control in the test section, thereby providing a more stable and reliable comprehensive test environment for high-altitude performance testing of aircraft components. Therefore, the in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components described in this invention can maintain a higher level of stability, consistency, and repeatability of key boundary parameters such as wind speed, air pressure, temperature, and humidity within the test section, which is beneficial for improving the operating condition maintenance capability and the reliability of test results in high-altitude performance testing.

[0104] Thirdly, the technical solution described in this invention, by arranging the main body of the wind tunnel inside a high-altitude environment simulation chamber, allows the wind field establishment, circulation recirculation, and test loading processes to be primarily completed within the chamber. Combined with isolation structures such as one-way valves, the pressure, temperature, and humidity parameter regulation systems are effectively separated. This system configuration reduces the number of trans-chamber interfaces and the crosstalk between different functional loops, effectively reducing the risks of leakage, backflow, and parameter crosstalk at interfaces, and improving the overall system's airtightness and functional isolation capabilities. Therefore, the in-chamber wind tunnel test platform system and method for high-altitude performance testing of aircraft components described in this invention not only improves the platform's sealing reliability but also enhances the stability of operating conditions during long-term continuous operation, further improving the engineering safety and operational reliability of the entire test system.

[0105] Fourth, the technical solution described in this invention, by setting up an environmental homogenization structure inside the high-altitude environment simulation chamber and combining it with a distributed sensor array and a unified control system, implements real-time monitoring, feedback adjustment, and coordinated control of the temperature, humidity, and related environmental parameters inside the chamber. This helps improve the consistency and uniformity of the environmental field distribution inside the chamber, effectively reducing temperature and humidity deviations between different areas within the chamber, and minimizing the additional impact of local environmental gradients on the test results of the specimens, thus providing a more stable and uniform environmental foundation for the test area. Therefore, the in-chamber wind tunnel test platform system and method for high-altitude performance testing of aircraft components described in this invention not only improves the controllability and consistency of environmental boundary conditions during high-altitude performance testing but also enhances the platform's adaptability to aircraft components of different types, sizes, and functional characteristics, thereby improving the versatility and engineering application value of the test platform.

[0106] Fifth, the technical solution described in this invention can not only support basic testing of the high-altitude performance of aircraft components, but also serve as a unified platform carrier for subsequent optimization technologies such as low-pressure steady flow control, anti-condensation control, wireless telemetry and control support, and pre-balancing and deceleration strategies. This provides a common foundation for further improvement, module expansion, and serial development of related subsystems, thereby enhancing the platform versatility, technical extensibility, and subsequent solution support capabilities of the in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components described in this invention. Attached Figure Description

[0107] Figure 1 This is a diagram of an in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components, as described in this invention.

[0108] Figure 2 This is a test system control logic diagram of an in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components, as described in this invention.

[0109] Figure 3 This is a front view of the cabin of an in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components, as described in this invention.

[0110] Figure 4 This is a rear view of the cabin of the in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components, as described in this invention.

[0111] Figure 5 This is a schematic diagram of the overall external structure of an in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components, as described in this invention.

[0112] Figure 6This is a schematic diagram of the integrated cross-sectional structure of the cabin of the in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components, as described in this invention.

[0113] Figure 7 This is a schematic diagram of the main channel of the in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components, as described in this invention.

[0114] Figure 8 This is a schematic diagram of the longitudinal sectional structure of the cabin of the in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components, as described in this invention.

[0115] Figure 9 This is a side view of the overall external structure of the cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components, as described in this invention.

[0116] [Attached image labels]

[0117] Environmental cabin insulation layer (1); cabin temperature and humidity sensor array (2); intelligent environmental homogenizing fan array 1 (3);

[0118] Anti-condensation electric heating film (4); wind tunnel wall temperature sensor (5); wind tunnel fan (6); contraction section (7); rectifier 1 (8);

[0119] Wind tunnel wind speed sensor (9); Test piece (10); Test section (11); Rectifier 2 (12); Wind tunnel gas temperature sensor (13).

[0120] Wind tunnel humidity sensor (14); wind tunnel pressure sensor (15); intelligent environmental homogenizing fan array 2 (16); one-way valve 1 (17);

[0121] Temperature control module (18); Pressure control module (19); Humidity control module (20); Check valve (21);

[0122] Environmental chamber body (22); industrial computer (23); wind tunnel shell (24); fully integrated wireless measurement and control support rod (25).

[0123] Six-dimensional force measurement unit (26); attitude adjustment mechanism (27); external clean gas input interface (28); UWB wireless communication interface (29).

[0124] Control interface (30); data acquisition card (31). Detailed Implementation

[0125] This invention provides an in-cabin wind tunnel test platform-level system for high-altitude performance testing of aircraft components. The constructed in-cabin wind tunnel test system not only meets the basic performance testing requirements of aircraft components under comprehensive high-altitude environmental conditions, but also forms an integrated platform architecture in terms of wind field construction, high-altitude environment simulation, parameter monitoring and feedback, and system collaborative control. Therefore, the in-cabin wind tunnel test platform-level system and method for high-altitude performance testing of aircraft components described in this invention can serve as a unified technical carrier for subsequent functional expansion and subsystem optimization.

[0126] Figure 1 This is a diagram illustrating an in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components, as described in this invention. Figure 1 As shown, the entire in-cabin wind tunnel test platform system comprises an upper-level high-altitude parameter control system, a central high-altitude environment simulation chamber, a wind tunnel test system located inside the high-altitude environment simulation chamber, and a two-way coupled environmental dynamic control system located on the outside of the chamber. The high-altitude parameter control system is connected to the high-altitude environment simulation chamber and is used to regulate the pressure, temperature, humidity, and cooling conditions within the chamber, thereby creating a low-pressure, low-temperature, and variable-humidity high-altitude simulated environment. The two-way coupled environmental dynamic control system is bidirectionally connected to the in-cabin wind tunnel test system and the environmental control system, and is used to uniformly receive multi-source sensor information and output flow stabilization control commands, anti-condensation control commands, and environmental homogenization control commands.

[0127] like Figure 1 As shown, the high-altitude environment simulation chamber is a closed pressure chamber that forms a controlled low-pressure high-altitude simulation space. Environmental homogenization fan arrays are installed on both sides of the chamber to create circulating disturbance reduction and temperature / humidity homogenization airflow, thereby reducing temperature and humidity differences and local environmental stratification within the chamber. The high-altitude parameter adjustment system achieves preset high-altitude conditions by inputting or extracting gas into the high-altitude environment simulation chamber and adjusting cooling or dehumidification conditions, and achieves dynamic stability through bidirectional feedback and coordination with the controller.

[0128] like Figure 1As shown, the wind tunnel test system arranged inside the high-altitude environment simulation chamber is preferably a closed-loop wind tunnel structure. Its outer perimeter is composed of a wind tunnel shell, and the interior is arranged in sequence along the main flow direction, including a wind tunnel fan (6), an adjustable contraction section (7), a pre-rectifier (8), a test section (11), a post-rectifier (12), and a return flow path. In the figure, the white arrows indicate the main flow direction of the test section, and the gray arrows indicate the direction of the return flow inside the chamber or the coupling flow of the external loop. The wind tunnel fan (6) is used to provide circulating power and regulate the circulating flow and pressure rise in the closed circulating air path; the adjustable contraction section (7) is used to adjust the local geometric acceleration capability by changing the effective cross-sectional area of ​​the throat; the pre-rectifier (8) is used to improve the uniformity of the incoming flow before entering the test section (11); the test section (11) is located in the middle of the main flow channel of the wind tunnel and provides a stable aerodynamic load environment for the test object (10) under low pressure and high altitude conditions; the post-rectifier (12) is arranged downstream of the test section and is used to correct the direction and redistribute the velocity of the exhaust flow, wake or non-uniform flow to reduce the impact of disturbances fed back to the upstream inlet boundary through the recirculation zone.

[0129] like Figure 1 As shown, in a preferred embodiment, the test piece (10) is installed inside the test section (11), and a wind tunnel wind speed sensor (9) is installed to obtain representative wind speeds; a gas temperature sensor (13), a humidity sensor (14), and a pressure sensor (15) are also installed in the adjacent area of ​​the test section to obtain the temperature, humidity, and pressure parameters required for dew point calculation; a wall temperature sensor (5) is installed on the wind tunnel shell (24), the outer wall of the test section (11), and other locations where cold spots are easily formed to obtain local wall temperature status in real time. An anti-condensation electric heating film (4) is also installed on the outer wall of the wind tunnel or the easily condensing area of ​​the test section. The electric heating film is preferably attached to the outer wall surface to provide heat supplementation to local cold spots without changing the shape of the inner wall flow channel boundary, thereby suppressing the formation of condensation or frost.

[0130] like Figure 1 As shown, the controller (23) in the bidirectional coupled environmental dynamic control system is connected to the wind speed sensor (9), wall temperature sensor (5), gas temperature sensor (13), humidity sensor (14), pressure sensor (15) and environmental homogenization sensor array, and is connected to the speed control actuator of the wind tunnel fan (6), the throat opening actuator of the adjustable contraction section (7), the power adjustment interface of the anti-condensation electric heating film (4) and the environmental homogenization fan array, respectively. On the one hand, the controller (23) adjusts the wind tunnel fan (6) and the adjustable contraction section (7) in coordination according to the deviation between the representative wind speed of the test section (11) and the target wind speed to achieve closed-loop stable flow of wind speed under low pressure conditions; on the other hand, it determines the risk of condensation according to the relationship between the wall temperature and the dew point temperature or frost point temperature, and drives the anti-condensation electric heating film (4) to perform local heat replenishment when the condensation safety margin drops to near the preset threshold.

[0131] Furthermore, such as Figure 1 As shown, this invention does not treat steady flow control and anti-condensation control as two independent single-loop controls, but rather constructs them into a multi-objective coupled control system through a unified supervisory control layer. Specifically, the controller (23) not only adjusts the speed of the wind tunnel fan (6) and the throat opening of the contraction section (7) based on the wind speed deviation, but also calculates the dew point temperature based on the gas temperature, humidity, and pressure, and calculates the condensation safety margin based on the difference between the wall temperature and the dew point temperature; subsequently, the controller uses the condensation safety margin as a constraint or joint objective quantity for steady flow control, and performs priority arbitration, execution boundary trimming, and mode switching control on the fan speed command, the contraction section opening command, and the heating film power command. In other words, an interconnected control network of "environmental parameter adjustment - wind tunnel steady flow construction - wall thermal management - loop coupling suppression" is formed in the high-altitude environment simulation chamber.

[0132] like Figure 1 As shown, from the working process, the high-altitude parameter adjustment system first establishes the target chamber pressure, target temperature, and target humidity; the environmental homogenization fan array homogenizes the large-scale temperature and humidity distribution inside the chamber; then, the wind tunnel fan (6) and the adjustable contraction section (7) establish the target wind speed of the test section (11) under the action of the controller (23); during the steady flow construction and test maintenance process, the controller (23) continuously monitors the representative wind speed, gas state, and wall temperature. When the wall temperature is found to be close to the dew point temperature or frost point temperature, the controller (23) drives the anti-condensation electric heating film (4) to perform local heat replenishment without significantly damaging the flow field quality of the test section, and can constrain the fan speed increase, contraction section adjustment rate, or target wind speed transition mode according to the condensation risk, so as to avoid the wall from further cooling due to enhanced convective heat transfer and entering the condensation risk zone. If necessary, the system can enter the condensation risk intervention mode or the degradation protection mode to prioritize the reliability of the test and the absence of condensation or frost on the wall.

[0133] like Figure 1 As shown, the in-cabin wind tunnel test platform system not only realizes the construction of a closed-loop wind tunnel with stable flow under low pressure, low temperature and variable humidity environment in the high-altitude environment simulation chamber, but also achieves the coordinated guarantee of the availability of the flow field in the test section and the safety of dew point anti-condensation through multi-source sensing, local heating and unified supervision and control, thereby improving the authenticity, repeatability and availability of high-altitude environment coupled test.

[0134] Figure 2 This is a test system control logic diagram of an in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components, as described in this invention. Figure 2As shown, the control logic of this invention is not an independent closed-loop control of a single parameter, but a multi-objective coupled control logic composed of an high-altitude parameter adjustment system, a high-altitude environment simulation chamber, a wind tunnel test system, and a two-way coupled environmental dynamic control system. This control logic involves at least four interrelated control sub-functions simultaneously: low-pressure high-altitude environment parameter establishment, chamber environment homogenization control, wind tunnel flow stabilization construction control, and wall dew point anti-condensation control, which are supervised and coordinated by a unified controller.

[0135] like Figure 2 As shown, the upper-level high-altitude parameter regulation system is used to comprehensively regulate the pressure, temperature, and humidity within the high-altitude environment simulation chamber, creating the target high-altitude environmental conditions. The high-altitude environment simulation chamber is equipped with target parameter uniformity control logic and an intelligent environmental homogenization fan, which, while establishing target chamber pressure, temperature, and humidity, reduces temperature and humidity gradients between different areas within the chamber, thereby improving the consistency of air conditions around the test area. This part constitutes the basic control layer of the external environment for wind tunnel testing.

[0136] Furthermore, Figure 2 The bidirectional coupled environmental dynamic control system shown on the right is the unified monitoring and coordination control part of this invention. This system is connected to the cabin temperature sensor, cabin humidity sensor, wind tunnel wall temperature sensor, and environmental homogenization fan control system, respectively. It receives real-time information on the cabin environmental status and wall thermal status, and coordinates the control of the environmental homogenization fan and the anti-condensation electric heating film. In other words, the bidirectional coupled environmental dynamic control system senses both the spatial temperature and humidity distribution within the high-altitude environmental simulation cabin and the localized cold spots on the wind tunnel walls, thus providing a basis for subsequent anti-condensation intervention and environmental homogenization control.

[0137] Furthermore, Figure 2 The wind tunnel testing system shown in the lower left corner primarily establishes steady-flow control logic around the target wind speed. Specifically, the wind tunnel testing system inputs the target wind speed and constructs the representative airflow velocity required for the test section by adjusting the wind tunnel fan speed. Simultaneously, the system collects measurements from wind tunnel gas temperature sensors, wind tunnel humidity sensors, and wind tunnel pressure sensors to obtain real-time thermal and humidity parameters of the air near the test section and calculate the dew point temperature accordingly. In this invention, the wind speed closed-loop control is not performed in isolation but is coupled with wall temperature, dew point temperature, and condensation risk assessment.

[0138] in addition, Figure 2The central decision node, "Whether the wall temperature reaches the condensation temperature," reflects the core logic of the anti-condensation control in this invention. Specifically, the controller calculates the dew point temperature based on the wind tunnel gas temperature, humidity, and pressure, or, in low-temperature frosting conditions, the frost point temperature. This dew point or frost point temperature is then compared with the local wall temperature detected by the wind tunnel wall temperature sensor to determine if there is a risk of condensation or frost formation. When the local wall temperature approaches, reaches, or falls below the dew point temperature, the controller outputs an anti-condensation intervention command, driving the anti-condensation electric heating film control system to activate or increase its power, providing localized heating to easily condensable areas on the outer wall of the wind tunnel shell or the outer wall of the test section. The logic block "Open the anti-condensation electric heating film" in the figure represents this active heating intervention process targeting localized cold spots.

[0139] Furthermore, Figure 2 The lower right section further illustrates the anti-condensation execution chain, whereby the wind tunnel wall temperature sensor feeds back wall temperature information to the anti-condensation electric heating film control system. The control system then controls the start / stop or power adjustment of the electric heating film based on the difference between the wall temperature and the dew point temperature. This control method is preferably a localized, zoned heating approach, meaning that only localized areas prone to cold spots are heated, rather than the entire environmental chamber is heated, thus avoiding unnecessary disturbances to the overall temperature field and flow field quality of the high-altitude environment simulation chamber and the test section.

[0140] at the same time, Figure 2 The right side of the diagram also illustrates the control logic between the cabin temperature sensor, cabin humidity sensor, and intelligent environmental homogenizing fan control system. The controller collects multi-point temperature and humidity distribution information to determine if there are temperature or humidity differences exceeding permissible ranges within the cabin. When significant spatial inhomogeneity is detected, the controller drives the intelligent environmental homogenizing fan to reduce large-scale temperature and humidity gradients within the cabin. This improves the consistency of air conditions around the test area and reduces the impact of local micro-environmental deviations on the accuracy of dew point calculation and condensation determination.

[0141] thus, Figure 2 The control logic shown can be summarized by the following coupling relationship:

[0142] First, the target cabin pressure, cabin temperature, and cabin humidity environment are established by the high-altitude parameter adjustment system;

[0143] Secondly, the uniformity of target parameters inside the cabin is improved by intelligent environmental homogenizing fans and environmental homogenizing control systems;

[0144] Furthermore, the wind tunnel testing system establishes the incoming flow of the test section based on the target wind speed;

[0145] At the same time, the controller calculates the dew point temperature based on the wind tunnel gas temperature, humidity and pressure, and judges the risk of condensation based on the comparison between the wall temperature and the dew point temperature.

[0146] When there is a risk of condensation, the controller drives the anti-condensation electric heating film to provide localized supplemental heating;

[0147] When the temperature and humidity distribution inside the cabin is uneven, the controller drives the environmental homogenization fan to reduce the spatial gradient.

[0148] Figure 2 The control logic shown does not treat "flow stabilization control" and "anti-condensation control" as two independent single loops. Instead, it couples target wind speed establishment, dew point risk assessment, local wall heating, and cabin environment homogenization through a unified supervisory control framework. This achieves coordinated control of flow stabilization, environmental homogenization, and dew point anti-condensation under low-pressure high-altitude environment simulation conditions. With this control logic, while maintaining the availability of target wind speed and flow field in the test section, it can suppress local condensation or frost on the wind tunnel walls, thereby improving the realism, reliability, and repeatability of the high-altitude environment coupled experiment.

[0149] Figure 3 This is a front view of the cabin of the in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components, as described in this invention.

[0150] like Figure 3 As shown, the high-altitude environment simulation chamber is a closed chamber structure. The cross-section of the chamber is preferably a rounded rectangle or a near-elliptical shape to balance pressure resistance, internal space utilization, and internal flow organization requirements. The interior of the chamber forms a controlled space for high-altitude environment simulation. This controlled space houses a wind tunnel testing system, environmental homogenization components, and related measurement and control components, thus forming an in-chamber wind tunnel testing platform under low-pressure, low-temperature, and variable humidity conditions.

[0151] exist Figure 3 In the illustrated embodiment, the wind tunnel testing system is located in the middle of the cabin and is mounted on the bottom of the cabin via a support frame. The support frame supports the main flow path and test section components of the wind tunnel, ensuring a stable position of the wind tunnel testing system relative to the cabin and reducing the impact of cabin vibration, installation deviations, or environmental disturbances on the incoming flow state of the test section. The wind tunnel testing system sequentially forms an inlet rectifying / contraction region, a test section region, and a downstream diffuser or discharge region along the main flow direction. The test section is used to accommodate the test object and establish the target incoming flow conditions, while the downstream diffuser or discharge section allows for a gradual transition of the flow discharged from the test section, reducing abrupt changes in local flow.

[0152] like Figure 3As shown, fan assemblies arranged in an array are respectively installed on the inner walls of the left and right sides of the cabin, preferably forming an environmental homogenization fan array. The environmental homogenization fan array is used to circulate and agitate the air inside the high-altitude environment simulation cabin, homogenize temperature and humidity, and regulate the local environment, thereby reducing temperature and humidity differences between different areas within the cabin and local environmental stratification. This fan array can be started, stopped, or operated at adjusted speed according to a preset strategy under the control of a controller, thus cooperating with the high-altitude parameter adjustment system to make the overall environmental parameters inside the cabin more uniform and reducing the impact of local hot spots or localized humidity enrichment on the wind tunnel test results.

[0153] like Figure 3 As shown, in a preferred embodiment, the top of the cabin is provided with multiple mounting interfaces, control mounting positions, or observation components for mounting sensors, lighting components, observation devices, cooling auxiliary devices, or other environmental control components. Wall temperature measurement points can also be arranged on the top and cabin walls to monitor whether localized cold spots form on the inner wall of the cabin, the outer wall of the wind tunnel shell, and the adjacent area of ​​the test section. For areas prone to condensation, an anti-condensation electric heating film is preferably installed on the corresponding outer wall to provide localized supplemental heating when the controller determines that the wall temperature is close to the dew point or frost point temperature.

[0154] like Figure 3 As shown, the wind tunnel testing system is arranged relatively centrally within the chamber, ensuring sufficient environmental recirculation space between it and the environmental homogenizing fan arrays on both sides. This arrangement facilitates the formation of an external recirculation channel for air within the chamber, enabling overall homogenization and control of the temperature, humidity, and pressure fields in conjunction with the internal environmental homogenizing fan arrays. Simultaneously, the central arrangement allows for the reservation of measurement and maintenance space around the test section to accommodate multi-source sensing units such as gas temperature sensors, humidity sensors, pressure sensors, and wall temperature sensors.

[0155] Furthermore, such as Figure 3 As shown, the arrangement of the cabin's front side embodies an important technical concept of this invention: the high-altitude environment simulation cabin is not merely a passive outer shell, but a coupled spatial carrier that functions in conjunction with high-altitude environmental parameter adjustment, cabin environment homogenization, wind tunnel flow stabilization, and dew point anti-condensation control. On one hand, the environmental homogenization fan arrays on the left and right sides of the cabin improve the overall uniformity of the cabin environment; on the other hand, the wind tunnel test system located in the center establishes the target wind speed and test section flow field under this uniform high-altitude environment background; simultaneously, for cold spots formed on the wind tunnel shell, the outer wall of the test section, and their adjacent areas, condensation or frost formation is suppressed through wall temperature measurement and localized heating. Thus, Figure 3 The front structure of the cabin shown reflects the integrated arrangement of "environmental homogenization - wind tunnel testing - anti-condensation thermal management" in the same cabin space in this invention.

[0156] like Figure 3 As shown, in actual operation, the high-altitude parameter adjustment system first establishes the pressure, temperature and humidity inside the cabin; then, the environmental homogenization fan array homogenizes the space inside the cabin; the wind tunnel test system establishes the target wind speed of the test section under the action of the unified controller; at the same time, the controller combines the temperature, humidity and pressure of the gas inside the cabin and the wall temperature to determine the risk of condensation or frost, and implements local wall heating when necessary. Figure 3 The overall layout of the cabin shown in the invention enables the coordinated operation of low-pressure high-altitude environment simulation, wind tunnel steady flow test and dew point anti-condensation control in a limited cabin space, thereby improving the realism of test conditions, test repeatability and system operation reliability.

[0157] Figure 4 This is a rear view of the cabin of the in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components, as described in this invention.

[0158] like Figure 4 As shown, the low-pressure high-altitude environment simulation chamber is a horizontal, closed pressure vessel structure. The chamber's shape is preferably a sealed pressure-bearing chamber consisting of end caps and a central cylindrical section. The chamber is installed on a foundation platform, which supports the high-altitude environment simulation chamber itself, external high-altitude parameter adjustment equipment, control cabinet, and auxiliary pipelines, thus forming a complete low-pressure high-altitude environment testing device. Figure 4 The view shown mainly reflects the overall external layout of the high-altitude environment simulation cabin, that is, the connection relationship between the cabin body and the external high-altitude parameter adjustment equipment, connecting pipelines, power supply and distribution and control components.

[0159] exist Figure 4 In the illustrated embodiment, the high-altitude environment simulation chamber is positioned slightly to the left of the center of the base platform. Its outer wall is equipped with multiple installation interfaces, observation interfaces, maintenance mounting positions, or control mounting bases to facilitate the installation of wall temperature measurement devices, external wall heating devices, observation components, and auxiliary pipelines. A sealed hatch is preferably provided on the side of the chamber for equipment installation, wind tunnel test system assembly, maintenance, and the entry and exit of test specimens. A reliable seal is achieved between the hatch and the chamber body via flanges, sealing rings, and fasteners, ensuring airtightness requirements under low-pressure high-altitude simulation conditions.

[0160] like Figure 4As shown, a group of high-altitude parameter regulation devices is arranged on the right side of the high-altitude environment simulation chamber. These devices may include refrigeration or heat exchange units, air extraction or pressure stabilization units, dehumidification or humidification units, air handling units, and supporting power and control components. This part of the equipment is connected to the high-altitude environment simulation chamber via external pipelines and is used to regulate the pressure, temperature, and humidity inside the chamber, thereby establishing and maintaining preset high-altitude environmental parameters. The blue and white pipelines in the figure can be used to represent different working fluid delivery loops or gas regulation loops, and their connection to the high-altitude environment simulation chamber reflects the fluid coupling relationship between the external parameter regulation system and the controlled environment inside the chamber.

[0161] like Figure 4 As shown, in a preferred embodiment, the external high-altitude parameter adjustment equipment is not used solely to change cabin pressure or temperature, but rather works in conjunction with the cabin wind tunnel stabilization system and anti-condensation control. Specifically, the external parameter adjustment equipment first establishes target cabin pressure, target cabin temperature, and target humidity; subsequently, the cabin wind tunnel test system establishes the target wind speed for the test section under this background environment; simultaneously, the controller calculates the dew point temperature or frost point temperature based on the cabin gas temperature, humidity, and pressure, and determines whether there is a risk of condensation or frost based on the wall temperature. When a condensation risk occurs, the controller can, on the one hand, drive the anti-condensation electric heating film to reheat localized cold spots on the outer wall, and on the other hand, correct the rate of change of environmental parameters through the external high-altitude parameter adjustment equipment, thereby suppressing the increased risk of condensation caused by rapid cooling, rapid depressurization, or humidity changes.

[0162] Figure 4 The arrangement of the rear of the chamber, as shown, also embodies an important feature of this invention: the high-altitude environment simulation chamber, the external parameter adjustment system, and the control system together constitute a closed, dynamically adjustable test environment platform. The chamber itself provides a controlled low-pressure test space; the external high-altitude parameter adjustment equipment provides background regulation capabilities for pressure, temperature, and humidity; the in-chamber wind tunnel test system establishes the stable inflow required for the test object; and the control system unifies environmental parameter adjustment, wind tunnel flow stabilization, and dew point anti-condensation control within a single control framework. Thus, Figure 4 This not only reflects the physical installation relationship of the equipment, but also the synergistic relationship among the three elements of "external environment establishment - in-cabin flow stabilization test - wall anti-condensation protection" in this invention.

[0163] Furthermore, Figure 4The arrangement of external piping and equipment facilitates the rapid establishment and dynamic adjustment of internal environmental parameters. For example, external refrigeration or air handling equipment can exchange heat, circulate, dehumidify, or replenish air within the cabin through piping connected to the cabin; extraction or pressure stabilization devices can be used to simulate cabin pressure levels corresponding to different altitudes; and control cabinets and power supply units can provide power and control to wind tunnel fans, contraction section actuators, anti-condensation electric heating films, environmental homogenization fan arrays, and various sensors. Thus, in Figure 4 Under the overall layout shown, the entire system can complete the establishment of the high-altitude environment, wind tunnel test operation, and anti-condensation protection around the same test objective.

[0164] In terms of operation, the external high-altitude parameter adjustment equipment is preferably used to establish a basic low-pressure high-altitude environment before the test begins. Subsequently, the in-cabin wind tunnel test system is started and the target wind speed is established. Throughout the test, the controller continuously receives signals from the wind tunnel wind speed sensor, gas temperature sensor, humidity sensor, pressure sensor, and wall temperature sensor, and implements coordinated control of the external parameter adjustment equipment, wind tunnel fan, adjustable contraction section, and anti-condensation electric heating film. When condensation risk or environmental fluctuations occur, the system can maintain stable test conditions through external parameter adjustment, local heating, and coordinated limiting of flow stabilization.

[0165] like Figure 4 As shown, the rear structure of the cabin and the arrangement of external equipment indicate that the present invention does not set up a wind tunnel in isolation in a pressure chamber, but rather constructs an integrated test system consisting of a high-altitude environment simulation cabin body, external high-altitude parameter adjustment equipment, an in-cabin wind tunnel test system, and a linkage control system. It can simultaneously meet the requirements of high-altitude environment simulation, wind tunnel flow stabilization construction, and dew point anti-condensation control under low pressure, low temperature, and variable humidity environments, thereby improving the authenticity, repeatability, controllability, and reliability of high-altitude environment coupling tests.

[0166] Figure 5 This is a schematic diagram of the overall external structure of an in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components, as described in this invention. Figure 5 As shown in the figure, this diagram illustrates the overall external layout of the experimental system of the present invention. The entire system mainly includes the main body of the cabin located in the middle, external parameter adjustment pipelines communicating with the cabin, a high-altitude parameter adjustment equipment group arranged on the rear side of the cabin, and a control and operation unit located on the front side of the cabin. Figure 5As shown, the cylindrical body referred to as the wind tunnel shell (24) is the main body of the test chamber or the chamber shell, which is preferably a horizontal, sealed, pressure-bearing structure used to create a low-pressure, high-altitude environment simulation space inside. The outer wall of the chamber is provided with multiple top interfaces, observation or installation interfaces, and side sealed doors, which facilitates the installation, maintenance, sensor placement, and loading and unloading of the test system. The doors are sealed by flanges and fasteners to ensure airtightness under low-pressure conditions.

[0167] like Figure 5 As shown, the cabin is connected to external regulating equipment via pipelines. Figure 5 The external pipes at the upper left and upper right are used to connect the cabin with the external environment regulation circuit to complete the functions of air extraction, air replenishment, pressure stabilization, heat exchange or humidity regulation. The one-way valve 2 (21) is preferably a valve, regulating valve or switching valve arranged on the connecting pipe, used to control the fluid on / off, flow regulation or operating condition switching, so as to cooperate with the control system to complete the dynamic regulation of cabin pressure, temperature and humidity. In addition, the box-type equipment arranged in groups at the rear of the cabin constitutes the external high-altitude parameter regulation equipment group. The one-way valve 17 (17) may include a refrigeration heat exchange unit, an air handling unit, an air extraction or pressure stabilization unit, a humidity regulation unit and corresponding power and control modules; its function is to establish the preset high-altitude simulation parameters before the start of the test, and to continuously correct the cabin pressure, temperature and humidity status according to the feedback signal during the test.

[0168] Figure 5 The front of the cabin is equipped with an operating console, a host computer, and a control cabinet, which constitute the human-machine interaction and control management part of the test system. Through this part, target test parameters can be input, control programs can be called, test status can be monitored, and test data can be recorded. The control cabinet is connected to the wind tunnel fan (6), the adjustable retractable section (7) actuator, the anti-condensation heating device, the environmental homogenization device, and various types of sensor signals inside the cabin, thereby realizing the unified coordination of wind tunnel flow stabilization control and dew point anti-condensation control inside the cabin.

[0169] From the overall layout perspective, Figure 5 This invention reflects the integrated platform structure of the system, consisting of "cabin body - external parameter adjustment equipment - connecting pipelines - control and operation unit". The cabin body provides a low-pressure high-altitude simulation space; the external parameter adjustment equipment is responsible for establishing and maintaining target environmental parameters; the connecting pipelines and valves realize the exchange and dynamic adjustment of media between the cabin and the external adjustment loop; the control and operation unit performs unified and coordinated control of the wind tunnel stabilization construction, anti-condensation and heat replenishment, and external environmental parameter adjustment within the cabin.

[0170] Furthermore, Figure 5The external structural layout shown illustrates that this invention is not simply an environmental chamber or a wind tunnel device, but rather integrates high-altitude environment simulation, wind tunnel testing, wall anti-condensation protection, and unified control and scheduling into a single test platform. Utilizing the overall structure of the test platform, in-chamber wind tunnel tests can be conducted under low pressure, low temperature, and variable humidity conditions, while simultaneously ensuring the availability of the flow field in the test section, the stability of environmental parameters, and a non-condensing or frosting state on the walls, thereby improving the realism, repeatability, and reliability of the tests.

[0171] Figure 6 This is a schematic cross-sectional view of the cabin integrated structure of the in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components, as described in this invention. Figure 6 As shown in the figure, this figure illustrates the overall integrated layout of the invention inside the high-altitude environment simulation chamber. An environmental chamber insulation layer (1) is provided on the outside of the environmental chamber body (22) to reduce heat exchange between the chamber and the outside environment and maintain the stability of the chamber environment under low pressure and low temperature conditions. A controlled high-altitude environment simulation space is formed inside the environmental chamber body (22), and an array of temperature and humidity sensors (2) is installed inside the chamber to obtain temperature and humidity distribution information at multiple points inside the chamber. Intelligent environmental homogenizing fan array 1 (3) and intelligent environmental homogenizing fan array 2 (16) are respectively arranged at both ends of the chamber body to circulate and stir the air inside the chamber, homogenize the temperature and humidity, and adjust the local environment to reduce the temperature and humidity difference in the space. An anti-condensation electric heating film (4) is set in the easily condensable area of ​​the chamber body or the outer wall of the wind tunnel, and works with the wind tunnel wall temperature sensor (5) to realize local wall temperature monitoring and heat replenishment control.

[0172] like Figure 6 As shown, a wind tunnel testing system is installed in the middle of the cabin, surrounded by a wind tunnel shell (24). Inside, along the main flow direction, there are wind tunnel fans (6), an adjustable contraction section (7), a pre-rectifier 1 (8), a test section (11), and a post-rectifier (12). Among them, the wind tunnel fans (6) are used to provide circulating power for the closed-loop air path; the adjustable contraction section (7) is used to adjust the local acceleration capability by changing the effective cross-sectional area of ​​the throat; the pre-rectifier 1 (8) is used to improve the uniformity of the incoming flow before entering the test section; the test section (11) provides a stable incoming flow condition for the test object (10) under low-pressure high-altitude environment; the post-rectifier (12) is used to rectify and redistribute the downstream discharge flow of the test section, reducing the impact of wake and disturbance on the upstream of the loop. The pre-rectifier or post-rectifier is preferably equipped with a honeycomb guide array (32) and a metal wire mesh rectification layer (33) to further improve the uniformity of the flow field and axial consistency.

[0173] like Figure 6As shown, a wind tunnel wind speed sensor (9) can be installed in the test section (11) to obtain representative wind speeds; at the same time, the test piece (10), the fully built-in wireless measurement and control support rod (25), the six-dimensional force measurement unit (26) and the attitude adjustment mechanism (27) are arranged to realize the support of the test piece, attitude adjustment, aerodynamic force measurement and wireless measurement and control. The wind tunnel gas temperature sensor (13), the wind tunnel humidity sensor (14) and the wind tunnel pressure sensor (15) are used to collect the gas state parameters required for dew point calculation. The industrial computer (23) is connected to each sensor and actuator through the control interface (30), the data acquisition card (31) and the UWB wireless communication interface (29) to realize the unified coordination of wind tunnel flow stabilization control, environmental parameter adjustment and anti-condensation control.

[0174] like Figure 6 As shown, the system can also be connected to external gas lines and environmental control equipment via one-way valve 1 (17), temperature control module (18), pressure control module (19), humidity control module (20), one-way valve 2 (21), and external clean gas input interface (28) to establish and maintain target pressure, temperature, and humidity inside the chamber. Therefore, Figure 6 This reflects the integrated coupling relationship of "high-altitude environment simulation - cabin environment homogenization - wind tunnel flow stabilization construction - local anti-condensation heating - multi-source measurement and control" in the same environmental cabin, thereby ensuring the authenticity, stability and condensation-free operation of wind tunnel tests under low pressure, low temperature and variable humidity conditions.

[0175] Figure 7 This is a schematic diagram of a partial structure of the main channel of the in-cabin wind tunnel test platform system for high-altitude performance testing of aircraft components, as described in this invention. Figure 7 The diagram shows the local structural arrangement of the wind tunnel test system in the mainstream direction. Along the airflow direction, the system consists of a wind tunnel fan (6), an adjustable converging section (7), a pre-rectifier 1 (8), a test section (11), and a post-rectifier (12). The wind tunnel fan (6) provides the circulating power for the closed-loop airflow path; the adjustable converging section (7) is used to change the local acceleration capability by adjusting the effective cross-sectional area of ​​the throat, thereby establishing the target wind speed required for the test section (11); the pre-rectifier 1 (8) is used to rectify the airflow before it enters the test section (11) to improve the uniformity of the incoming flow and reduce lateral disturbances.

[0176] like Figure 7As shown, the test section (11) is equipped with a test piece (10) for conducting aerodynamic loading or environmental coupling tests under low-pressure high-altitude conditions; a wind tunnel wind speed sensor (9) is installed near the test section to acquire representative wind speed signals as feedback for wind speed closed-loop control. A post-rectifier (12) is installed downstream of the test section to correct the direction and redistribute the velocity of the wake or non-uniform discharge flow after passing through the test piece (10), so as to reduce the transmission of downstream disturbances to the recirculation area and the upstream inlet boundary.

[0177] like Figure 7 As shown, a wind tunnel gas temperature sensor (13), a wind tunnel humidity sensor (14), and a wind tunnel pressure sensor (15) are arranged in the downstream adjacent area of ​​the test section to obtain the gas temperature, humidity, and pressure parameters of the corresponding working conditions of the test section in real time, so as to calculate the dew point temperature, frost point temperature, and air density; a wind tunnel wall temperature sensor (5) is set at the front end to monitor the local wall temperature of the wind tunnel shell in order to determine whether there is a risk of condensation or frost.

[0178] like Figure 7 As shown, the integrated arrangement of "power drive - geometric acceleration - pre-rectification - test section measurement and control - post-rectification - temperature, humidity and pressure detection" in the main channel of the wind tunnel in this invention realizes the linkage control of stable flow construction, flow field quality control and dew point anti-condensation in the test section under low pressure and high altitude environment.

[0179] Figure 8 This is a longitudinal sectional view of the cabin structure of the in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components, as described in this invention. Figure 8 The figure shows the longitudinal cross-sectional layout of the interior of the high-altitude environment simulation chamber along the main direction of the wind tunnel. The outermost layer is the environmental chamber body (22), which is preferably provided with an environmental chamber body insulation layer (1) to reduce heat exchange between the chamber and the outside world and maintain the stability of the chamber environment under low pressure and low temperature conditions. Intelligent environmental homogenizing fan array 1 (3) and intelligent environmental homogenizing fan array 2 (16) are respectively set on both sides of the chamber body to circulate and stir the air in the chamber, homogenize the temperature and humidity, and regulate the local environment; the anti-condensation electric heating film (4) is preferably set on the inner side of the chamber body or the corresponding easy condensation area on the outer wall of the wind tunnel to provide heat supplementation for local cold spots; the wind tunnel wall temperature sensor (5) is used to monitor the wall temperature at the corresponding position in real time to determine whether there is a risk of condensation or frost. One-way valve 1 (17) and one-way valve 2 (21) are also shown on the upper sides of the figure to connect with the external environmental regulation pipeline and control the unidirectional flow of the medium.

[0180] like Figure 8As shown, the wind tunnel test system is arranged in the middle of the cabin, and the outer part is the wind tunnel shell (24). Inside, along the main flow direction, the wind tunnel fan (6), the adjustable contraction section (7), the pre-rectifier 1 (8), the wind tunnel wind speed sensor (9), the test section (11), and the post-rectifier (12) are arranged in sequence. Among them, the wind tunnel fan (6) is used to provide the circulating power of the main flow of the closed loop wind tunnel; the adjustable contraction section (7) changes the local acceleration capability by adjusting the effective cross-sectional area of ​​the throat to establish the target wind speed of the test section; the pre-rectifier 1 (8) is used to rectify the airflow before it enters the test section to improve the uniformity of the incoming flow; the wind tunnel wind speed sensor (9) is used to obtain the representative wind speed of the test section as the feedback quantity for wind speed closed-loop control; the test section (11) provides a stable incoming flow and high-altitude environment coupling test space for the test object (10); the post-rectifier (12) is used to correct the direction and redistribute the velocity of the downstream outflow of the test section to reduce the impact of wake and disturbance on the upstream of the loop.

[0181] Figure 8 This reflects the integrated relationship of "overall environmental conditioning of the environmental chamber - environmental homogenization within the chamber - stable flow construction of the wind tunnel main duct - local anti-condensation and heat replenishment of the walls" on the same longitudinal section within the chamber in this invention. The technical solution described in this invention improves the spatial uniformity of parameters within the chamber through an environmental homogenization fan array, establishes a stable flow field in the test section through wind tunnel fans, a contraction section, and a rectifier, and suppresses condensation or frost through wall temperature measurement and local heating, thereby ensuring the authenticity, stability, and reliability of wind tunnel tests in low-pressure, high-altitude environments.

[0182] Figure 9 This is a side-view external structural diagram of the in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components according to the present invention, showing the overall side-view external layout structure of the test system of the present invention. The system mainly includes the environmental cabin body (22), the in-cabin test section where the wind tunnel shell (24) is located, the external environmental conditioning pipeline connected to the environmental cabin, and the external parameter adjustment equipment and control equipment located on one side of the cabin body.

[0183] like Figure 9 As shown, the large horizontal sealed chamber in the middle is the environmental chamber chamber (22). It is preferably provided with an environmental chamber insulation layer (1) on its outer side to reduce heat exchange between the chamber and the outside world and maintain the stability of the chamber environment under low pressure and low temperature conditions. The top of the chamber is provided with multiple installation interfaces or observation interfaces, and the side walls of the chamber are provided with sealed doors to facilitate the installation, maintenance and loading / unloading of the internal wind tunnel test system and the test components. The wind tunnel shell (24) is arranged inside the environmental chamber chamber (22) to form the main channel of the closed-loop wind tunnel and to support the wind tunnel fan (6), adjustable shrink section (7), pre-rectifier 1 (8), test section (11) and post-rectifier (12).

[0184] like Figure 9 As shown, external pipelines connected to the environmental chamber are installed on both sides above. One-way valve 1 (17) is installed on the left pipeline, and one-way valve 2 (21) is installed on the right pipeline. The one-way valves are used to control the unidirectional flow of the medium. Together with the external clean gas input interface (28), pressure control module (19), temperature control module (18), and humidity control module (20), the pressure, temperature, and humidity inside the chamber can be established and dynamically adjusted. Through this external pipeline system, clean gas can be input into the environmental chamber, and air can be pumped or pressure stabilized. The low-pressure high-altitude environment can be quickly established and maintained according to the experimental requirements.

[0185] like Figure 9 As shown, the box-type equipment arranged in groups on the right preferably constitutes an external high-altitude parameter adjustment system, which may include a temperature control module (18), a pressure control module (19), a humidity control module (20), and its auxiliary power equipment. This part of the equipment is connected to the environmental chamber body (22) through pipelines and is used to comprehensively adjust the air state inside the chamber, so that the interior of the environmental chamber forms a high-altitude simulation environment that meets the test requirements. The industrial computer (23) and related operating stations set on the left are used to realize human-computer interaction, test parameter input, status monitoring, and control command issuance; the industrial computer (23) is connected to various sensors and actuators inside the chamber through the control interface (30), data acquisition card (31), and UWB wireless communication interface (29).

[0186] Figure 9 This mainly reflects the overall side-view layout of the system in this invention, consisting of "environmental chamber body - external environmental conditioning pipeline - one-way valve control - external parameter adjustment equipment - industrial computer control terminal". This structure indicates that this invention is not a standalone environmental chamber device, but rather an integrated experimental platform that combines high-altitude environment establishment, in-chamber wind tunnel testing, parameter adjustment, and control management. This provides a complete hardware foundation for wind tunnel flow stabilization construction and dew point anti-condensation linkage control under low-pressure, low-temperature, and variable humidity conditions.

[0187] Furthermore, based on the in-cabin wind tunnel test platform system for high-altitude performance testing of aircraft components provided by this invention, targeted improvements and integrated development can be carried out on key technologies such as stable flow control under low-pressure conditions, anti-condensation regulation, wireless telemetry and control support structure, and pre-balancing and deceleration control strategies. Since subsequent optimizations are all based on the same integrated test platform framework, the in-cabin wind tunnel test platform system for high-altitude performance testing of aircraft components provided by this invention not only has direct experimental application value but also possesses good platform scalability, technical carrying capacity, and a foundation for serial development, which is conducive to forming technical solutions for different test objectives and functional requirements. Therefore, the in-cabin wind tunnel test platform system for high-altitude performance testing of aircraft components provided by this invention (as a parent system) can provide a unified parent and implementation foundation for the step-by-step improvement, modular upgrade, and serial expansion of subsequent related subsystems, demonstrating strong platform foundation and technology incubation value.

[0188] The present invention discloses an in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components. The goal is to embed a closed-loop wind tunnel into a sealed high-altitude environment simulation chamber and coordinate it with temperature, pressure, and humidity control systems, environmental homogenization structures, isolation structures, and a unified control system. This allows the wind field and the high-altitude environmental field to be coupled and established in the same controlled space, thereby forming an integrated test platform for high-altitude comprehensive performance verification of aircraft components.

[0189] Furthermore, compared to existing solutions that separate the wind tunnel from the environmental chamber or only add temperature control components to the atmospheric pressure wind tunnel, the difference of the in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components described in this invention is the establishment of a four-layer collaborative system: "environmental chamber body—in-cabin wind tunnel—parameter adjustment—closed-loop control." This four-layer collaborative system, by embedding the entire wind tunnel within a high-altitude environmental simulation chamber and forming a closed-loop air path, combined with the linkage compensation of the adjustable contraction section and fan speed, multi-point temperature and humidity homogenization control, and anti-condensation control based on dew point criteria, achieves the synchronous and stable construction of the test flow field and environmental field under low pressure, low temperature, and high humidity conditions. The four-layer collaborative system of this invention is a systematic solution that forms mutual dependence and synergy under the constraints of multi-physics field coupling.

[0190] From a hierarchical perspective, the in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components described in this invention are divided into four levels: the environmental cabin body layer, the in-cabin wind tunnel layer, the parameter adjustment layer, and the closed-loop control layer. The environmental cabin body layer provides a controllable high-altitude boundary, the in-cabin wind tunnel layer provides controlled airflow loads, the parameter adjustment layer establishes and maintains temperature, pressure, and humidity conditions, and the closed-loop control layer couples the environmental cabin body, the in-cabin wind tunnel system, and the parameter adjustment into a dynamically stable test system. The environmental chamber consists of a sealed chamber, an insulation layer, a temperature and humidity sensor array, and an intelligent environmental homogenization fan array, forming a uniform boundary space suitable for high-altitude environment simulation. The wind tunnel layer inside the chamber, through a closed-loop wind tunnel, an adjustable contraction section, a honeycomb-wire mesh composite rectifier, a test section, an anti-condensation heating film, and a wireless measurement and control support rod, enables the establishment of high-quality airflow loads and high-precision measurement under low-pressure conditions. The parameter adjustment layer establishes and maintains the high-altitude environmental parameters inside the chamber through temperature, pressure, and humidity control modules and one-way valves. The closed-loop control layer uses an industrial computer and various sensors to coordinate and control wind speed, chamber pressure, temperature, humidity, dew point, and environmental uniformity in real time.

[0191] The present invention discloses an in-cabin wind tunnel test platform system and method for high-altitude performance testing of aircraft components. The four layers of the environmental cabin body layer, the in-cabin wind tunnel layer, the parameter adjustment layer, and the closed-loop control layer are organized around the specific target of the high-altitude multi-parameter coupled test cabin. They form an integrated system that can operate stably for a long time, resist low-pressure wind speed attenuation, prevent condensation, and maintain a tight seal. It can achieve systematic synergy in environmental setup, flow field formation, condensation suppression, sealing measurement, and dynamic stable operation, thus constituting an integrated technical solution that is different from the "wind tunnel + environmental cabin" in the prior art.

[0192] Environmental cabin body layer: establishing the spatial location of the high-altitude environment

[0193] The environmental chamber body layer is used to construct and maintain a high-altitude background environment with low pressure, low temperature and set humidity in a closed space, and to suppress the macroscopic temperature and humidity gradient caused by the operation of the built-in wind tunnel in the chamber through multi-point sensing and active homogenization mechanism, thereby providing stable and consistent environmental boundary conditions for the test section.

[0194] The environmental chamber body layer is an environmental matrix that actively maintains spatial consistency. It is an active homogenization logic for wind tunnel disturbances within the chamber: as the high-altitude environmental background construction unit on which the wind tunnel test system relies for operation, it is used to establish and stably maintain a comprehensive environmental field under low pressure, low temperature and set humidity conditions in a closed space.

[0195] The environmental chamber itself integrates a continuously operating closed-loop wind tunnel. Therefore, the environment inside the chamber is affected not only by temperature, air pressure, and humidity regulation processes, but also by the coupled effects of localized heat release, flow disturbances, humidity migration, and spatial stratification caused by wind tunnel operation. To ensure that the specimen remains under realistic and consistent high-altitude environmental boundary conditions throughout the experiment, this invention establishes a highly stable environmental maintenance foundation through a sealed chamber and insulation layer. A multi-point distributed temperature and humidity sensor array provides real-time sensing of the spatial distribution of temperature and humidity within the chamber. Furthermore, an intelligent environmental homogenizing fan array, arranged in upper and lower sections or symmetrically, dynamically starts, stops, and adjusts its speed based on temperature and humidity difference thresholds, thereby actively suppressing and homogenizing the macroscopic temperature and humidity gradient within the chamber. Thus, the environmental chamber itself does not achieve the static maintenance of a single environmental parameter, but rather, under the continuous operation of the built-in wind tunnel, actively constructs, corrects in real-time, and stably maintains the large-scale background environmental field surrounding the specimen, providing stable and consistent high-altitude environmental boundary conditions for the test section. The environmental chamber body layer further addresses the issues of flow disturbance, heat redistribution, and humidity migration caused by the operation of the closed-loop wind tunnel within the chamber by introducing an active homogenization mechanism based on spatial distribution perception.

[0196] Specifically, the environmental chamber's main body layer does not rely on single-point measurements or average values ​​for environmental control. Instead, it uses a multi-point distributed temperature and humidity sensor array to acquire real-time temperature and humidity field distribution characteristics in different areas within the chamber, thereby identifying local temperature differences, humidity differences, and the degree of environmental stratification. When the temperature and humidity deviation between any areas exceeds a set threshold, it controls the intelligent environmental homogenizing fan arrays arranged in upper and lower zones or symmetrically to dynamically start, stop, and adjust their speed, actively reducing and reshaping the macroscopic temperature and humidity gradient within the chamber. Therefore, the function of the environmental chamber's main body layer is no longer limited to providing a sealed volume and maintaining a static environment. Instead, it can perform real-time correction and stable maintenance of the background environmental field around the specimen under continuous operation of the built-in wind tunnel, ensuring the consistency of the spatial distribution of external boundary conditions in the test section. This provides a stable and reliable high-altitude environmental foundation platform for in-chamber wind tunnel coupled testing.

[0197] The core task of the environmental chamber's main body is to provide a basic physical space that can be sealed, insulated, and withstand high-altitude environments such as low pressure, low temperature, and high humidity. The environmental chamber's main body is responsible for constructing and maintaining the stable background environment. It first establishes a controllable, sealed high-altitude environment around the system, allowing subsequent wind tunnel tests to run within a pre-set low-pressure, low-temperature, and specific humidity background field. Thus, the wind tunnel layer inside the chamber provides the local test flow, while the environmental chamber's main body provides the overall boundary environment of the test specimen; only when these two are combined can the conditions approximate real high-altitude service conditions.

[0198] The environmental chamber's main body is designed to establish and maintain a stable and uniform high-altitude environmental background field within a sealed space, allowing subsequent wind tunnel tests to be conducted under low-pressure, low-temperature, high-humidity, or low-humidity conditions, rather than at normal pressure and temperature. The core of the environmental chamber's main body is to transform the environmental chamber from a static container into an environmental matrix capable of providing a stable background field for the continuous operation of the wind tunnel within. Furthermore, a continuously operating closed-loop wind tunnel is embedded within the environmental chamber's main body. Therefore, the interior of the chamber is no longer a static environment but is affected by heat sources, pressure fluctuations, humidity migration, and localized turbulence generated by the wind tunnel's operation.

[0199] In terms of functional division, the environmental cabin body layer is responsible for establishing the background environment and addressing spatial unevenness.

[0200] Establishing a background environment means that the environmental chamber body layer stabilizes high-altitude environmental parameters such as low pressure, low temperature, high humidity or low humidity through a sealed chamber and thermal insulation structure.

[0201] To address spatial non-uniformity, the environmental chamber's main body layer uses a multi-point temperature and humidity sensor array to detect temperature and humidity differences at different locations within the chamber. Then, intelligent environmental homogenizing fan arrays, arranged vertically or symmetrically, smooth out these macroscopic gradients. These fans are designed to maintain a consistent environmental background throughout the chamber, preventing significant environmental drift in the upper, lower, near-wall, and specimen-surrounding areas once the wind tunnel is operational.

[0202] The environmental cabin body layer includes a high-altitude environment simulation cabin and an internal environment homogenization component; wherein the high-altitude environment simulation cabin includes an environmental cabin body (22) and an environmental cabin body insulation layer (1); wherein the internal environment homogenization component includes an intelligent environment homogenization fan array 1 (3), an intelligent environment homogenization fan array 2 (16) and a temperature and humidity sensor array (2).

[0203] The high-altitude environment simulation chamber is not an open test area, but a closed chamber that can maintain low air pressure, low temperature and set humidity; the high-altitude environment simulation chamber is a specially reconstructed environment for "in-cabin wind tunnel operation" and is optimized for the working conditions of the built-in wind tunnel; the thermal insulation layer (1) of the environment chamber is not a simple shell, but is designed to reduce heat exchange and maintain environmental stability under low temperature conditions.

[0204] The cabin environment homogenization component forms a multi-point temperature and humidity sensor array within the cabin. This array does not perform single-point measurements but rather multi-point distributed sampling to determine the uniformity of the cabin space. The cabin environment homogenization component is specifically designed to address the disturbance of the background field caused by the wind tunnel circulation. It features a symmetrical homogenization fan array, with any two-point temperature or humidity difference thresholds serving as the trigger condition. The cabin environment homogenization component employs a layered flow field management approach, where the wind tunnel interior is responsible for local high-quality test flow, while the cabin interior is responsible for macroscopic environmental field homogenization.

[0205] The cabin environment homogenization component features an intelligent environment homogenization fan array (intelligent environment homogenization fan array 1 (3) and intelligent environment homogenization fan array 2 (16)) arranged vertically and symmetrically. The intelligent environment homogenization fan array is not a fan that is always on, but starts, stops and adjusts its speed according to the temperature and humidity differences at multiple points based on thresholds. The function of the intelligent environment homogenization fan array is to smooth out the macro temperature and humidity gradient inside the cabin.

[0206] The environmental chamber body layer and the wind tunnel layer inside the chamber are in a layered relationship: the environmental chamber body layer is responsible for the large-scale environmental background field outside the specimen; it solves the problem of "whether this airflow is in a real and consistent high-altitude environment"; the wind tunnel layer inside the chamber is responsible for the high-quality test flow in the local area of ​​the specimen, and solves the problem of "whether there is an airflow that meets the requirements".

[0207] In-cabin wind tunnel layer: Applying stable and measurable airflow loads to the in-cabin environment.

[0208] The wind tunnel layer inside the cabin is used to establish a closed-loop test airflow in a closed high-altitude environment. Through a combination of measures such as fan drive, adjustable contraction section compensation, compound rectification and anti-condensation protection, a stable, uniform and measurable test flow field is maintained under low pressure, low temperature and variable humidity background conditions, thereby providing the specimen with local aerodynamic loading conditions under a real high-altitude environment.

[0209] The core task of the wind tunnel layer inside the cabin is to establish a closed-loop, controllable wind speed, and guaranteed flow field quality wind tunnel test channel inside the sealed high-altitude environment cabin, which is used to apply real aerodynamic loads to the test specimens.

[0210] The in-cabin wind tunnel layer is used to reconstruct a controllable, measurable, and long-term stable local test flow field in an established high-altitude, low-density background environment. The in-cabin wind tunnel layer is responsible for generating test airflow and maintaining flow field quality. The environmental chamber body layer addresses the macroscopic background environment of the test specimen and is responsible for placing the test in a high-altitude environment. The in-cabin wind tunnel layer addresses whether there is a high-quality incoming flow in the local area of ​​the test specimen that meets the test requirements. The in-cabin wind tunnel layer is responsible for ensuring that the test specimen is truly subjected to verifiable aerodynamic loading in this high-altitude environment.

[0211] The core of the in-cabin wind tunnel layer is to embed the entire wind tunnel within the high-altitude environment simulation chamber, making it a closed-loop subsystem operating in a low-pressure, low-temperature, and variable-humidity environment. The in-cabin wind tunnel must address a series of new coupling problems: maintaining wind speeds in low-density media is difficult; local disturbances within the chamber can negatively impact the wind tunnel inlet conditions; condensation easily occurs on the shell and specimen surfaces under low temperature and high humidity; and traditional through-cabin wiring can compromise the system's seal. Therefore, the in-cabin wind tunnel layer is essentially a systematic reconstruction of "how a wind tunnel can effectively operate within a high-altitude simulation chamber," rather than simply transplanting an existing wind tunnel into the chamber.

[0212] In terms of functional division, the cabin wind tunnel layer is mainly responsible for establishing a closed-loop test airflow, maintaining the target wind speed under low-pressure conditions, maintaining the flow field quality of the test section, and ensuring the sustainable operation of the wind tunnel in complex environments. The establishment of a closed-loop test airflow involves the wind tunnel layer within the chamber forming an independent circulating air path through the wind tunnel fan, contraction section, rectifier, and test section. This prevents direct exchange of the test airflow with the outside environment, thus preserving the established temperature, pressure, and humidity background within the chamber. Maintaining the target wind speed under low-pressure conditions is achieved through the wind tunnel layer's linkage compensation between the fan speed and the adjustable contraction section throat cross-sectional area, overcoming the decrease in gas density and attenuation of test wind speed caused by low pressure. Maintaining the flow field quality in the test section involves the wind tunnel layer using a composite rectifying structure composed of a honeycomb guide array and multi-layer metal wire mesh to suppress turbulence and improve the uniformity of flow velocity distribution, ensuring the test airflow remains measurable and repeatable under low-density conditions. Ensuring the wind tunnel's sustainable operation in complex environments involves the wind tunnel layer employing an anti-condensation design with an electrically heated film linked to wall temperature and dew point, as well as fully integrated wireless monitoring and control supports to prevent cables penetrating the chamber from damaging the seal, ensuring stable and effective operation of the wind tunnel under low-temperature and high-humidity conditions.

[0213] The in-cabin wind tunnel layer integrates the wind tunnel within the high-altitude cabin. This is not merely a change in location, but a transformation of the overall system architecture. The challenge in establishing the in-cabin wind tunnel layer lies not in the individual components such as the fan, rectifier, and heating membrane, but in organizing these individual components into a dedicated wind tunnel subsystem designed for operation within the high-altitude cabin. The in-cabin wind tunnel layer adopts an architecture of "environmental cabin as the parent system and wind tunnel as the embedded circulation subsystem," incorporating targeted measures such as low-pressure wind speed dual-actuator compensation, low-pressure flow field quality maintenance, anti-condensation linkage protection, and wireless built-in measurement and control. This indicates that the in-cabin wind tunnel layer is no longer an ordinary wind tunnel device, but a core loading platform specifically designed for coupled testing in high-altitude environments. This architectural change necessitates greater attention to maintaining wind speed under low pressure, the impact of local disturbances within the cabin on the overall environment, and the increased complexity of condensation, recirculation, sealing, and measurement wiring.

[0214] The wind tunnel layer inside the cabin includes a wind tunnel fan (6), an adjustable retractable section (7), a rectifier 1 (8), a test section (11), a wind tunnel shell (24), a wind tunnel wind speed sensor (9), an anti-condensation electric heating film (4), a wind tunnel wall temperature sensor (5), a wind tunnel gas temperature sensor (13), a wind tunnel humidity sensor (14), a wind tunnel pressure sensor (15), a fully built-in wireless measurement and control support rod (25), a six-dimensional force measurement unit (26), and an attitude adjustment mechanism (28).

[0215] The wind tunnel fan (6) is built into the high-altitude environment simulation chamber. The wind tunnel layer inside the chamber forms a closed circulation air path, that is, the wind tunnel circulation gas does not directly exchange with the outside, thus avoiding damage to the set environment inside the chamber. The wind tunnel layer inside the chamber forms a combination of "wind tunnel fan (6), adjustable contraction section (7), rectifier 1 (8), and test section (11)," which forms a dual actuator collaborative compensation for the flow characteristics of low-density media. In low-pressure, low-temperature, and variable-humidity environments, the turbulence and uniformity are still controlled within the testable range. A wind speed sensor is installed in the test section (11) to perform closed-loop correction of the fan speed. An anti-condensation electric heating film (4) is installed on the outer wall of the wind tunnel shell (24) and is linked with the wall temperature or temperature and humidity information to prevent condensation. The fully built-in wireless measurement and control support rod (25) can avoid damage to the sealing performance by the cable passing through the chamber.

[0216] The environmental cabin body layer and the cabin wind tunnel layer are in a hierarchical relationship: the environmental cabin body layer is the parent system, responsible for "whether the high-altitude background environment is real and consistent" and providing external boundary conditions; the cabin wind tunnel layer is an embedded circulation subsystem, responsible for "whether the test flow is stable, uniform and measurable" and providing local aerodynamic load conditions; the coupling between the environmental cabin body layer and the cabin wind tunnel layer during operation ensures that all test specimens experience a coupled test environment that is close to the real high-altitude service state.

[0217] Parameter regulation layer: Establishment and maintenance of upper-level thermo-baro-humidity boundary

[0218] The parameter adjustment layer is used to perform coordinated preprocessing of temperature, pressure and humidity on the gas entering the high-altitude environment simulation chamber. Combined with one-way isolation, pre-balancing and slow-stop operation management, it continuously establishes, inputs and maintains the target high-altitude background parameters under the disturbance conditions of wind tunnel operation in the chamber. The parameter adjustment layer is responsible for establishing and maintaining the target high-altitude environmental parameters for the chamber, namely the generation and compensation of the three background field parameters of air pressure, temperature and humidity.

[0219] The parameter adjustment layer is used to perform coordinated preprocessing of temperature, pressure and humidity on the gas entering the high-altitude environment simulation chamber. Combined with one-way isolation and pre-balancing and slow-stop operation management, it continuously establishes, inputs and maintains the target high-altitude background parameters under the disturbance conditions of wind tunnel operation in the chamber. The parameter regulation layer is a subsystem designed for the supply and dynamic maintenance of background parameters in high-altitude environment-wind tunnel coupled testing conditions. It continuously generates, inputs, and stably maintains the low pressure, low temperature, and set humidity background field required for the test. The parameter regulation layer consists of temperature control, pressure control, and humidity control modules working together. It performs integrated temperature-pressure-humidity pretreatment on the gas entering the high-altitude environment simulation chamber, ensuring that the working medium entering the chamber reaches the target state before input, thus establishing the high-altitude environment background parameters from the source. At the same time, the parameter regulation layer has taken into account the local pressure fluctuations, heat redistribution, and humidity migration that may occur when the closed-loop wind tunnel inside the chamber is running continuously. Therefore, the parameter regulation layer also isolates the system boundary through a one-way valve between itself and the high-altitude environment simulation chamber, suppressing the backflow of gas inside the chamber to the inlet or outlet of the regulation system, reducing the reverse impact of internal circulation disturbances on the accuracy and stability of parameter regulation, thereby ensuring the independence and controllability of the background parameter supply process.

[0220] The core task of the parameter regulation layer is to establish and maintain the temperature, pressure, and humidity boundary conditions required for high-altitude environment simulation, and to provide stable input to the environmental chamber body layer. The parameter regulation layer is responsible for "generating, inputting, and compensating for the high-altitude background field"; the environmental chamber body layer is responsible for maintaining the environment inside the chamber, and the wind tunnel layer inside the chamber is responsible for establishing the local experimental flow field within that environment; while the parameter regulation layer addresses a more upstream issue, namely how the three background parameters of low pressure, low temperature, and set humidity are established, continuously fed into the chamber, and maintained under dynamic disturbances. In other words, the environmental chamber body layer and the wind tunnel layer inside the chamber are more focused on "bearing and loading," while the parameter regulation layer is responsible for "supply and regulation."

[0221] The key to the parameter regulation layer is organizing the temperature, pressure, and humidity boundary conditions into a high-altitude parameter regulation subsystem oriented towards the coupled operating conditions of the wind tunnel within the cabin. In this invention, these three boundary conditions not only need to be established simultaneously within the same confined space, but also must coexist with the continuously operating closed-loop wind tunnel within the cabin, and dynamically compensate for disturbances caused by wind tunnel operation. Therefore, the parameter regulation layer forms a composite supply system capable of collaboratively outputting "temperature-pressure-humidity" background parameters under coupled operating conditions.

[0222] The challenge in establishing the parameter regulation layer lies in organizing individual components such as temperature control, pressure control, humidity control, or check valves into a parameter supply and boundary management system dynamically coupled with the wind tunnel within the cabin. In this invention, the parameter regulation layer emphasizes the coordinated establishment and dynamic maintenance of the three parameters within the same platform and cabin area; check valves (17) and (21) are no longer merely safety accessories, but boundary isolation components that maintain the stability of the parameter regulation subsystem; pre-balancing and slow-stop are no longer just operating habits, but process control logic proposed for the dynamic behavior of the coupled system. This indicates that the parameter regulation layer is a background parameter supply platform specifically designed for high-altitude environment-wind tunnel coupled testing.

[0223] Furthermore, the parameter adjustment layer not only establishes the target environmental parameters but also manages the operating conditions throughout the entire test process. Specifically, before the test starts, a pre-balancing process is used to adjust the cabin air pressure, temperature, and humidity to the target values ​​and maintain them stable before starting the cabin wind tunnel system to avoid interference from wind tunnel operation during the environmental setup phase. After the test, a slow-stop process is used to first release the test airflow loading and then remove the environmental parameter adjustments after a delay to reduce the risks of pressure fluctuations, temperature and humidity drift, and condensation caused by the shutdown transient. Thus, the parameter adjustment layer is a background parameter supply platform that works in conjunction with the environmental cabin body layer and the cabin wind tunnel layer. The environmental cabin body layer is responsible for the bearing and homogenization of the background environment, the cabin wind tunnel layer is responsible for the establishment and maintenance of the local test flow field, and the parameter adjustment layer is responsible for the generation, input, and dynamic compensation of background environmental parameters. Together, these three constitute a comprehensive test system that can stably maintain the target high-altitude operating conditions under coupled disturbance conditions.

[0224] The parameter adjustment layer, the environmental cabin body layer, and the in-cabin wind tunnel layer are in a layered relationship: the environmental cabin body layer is responsible for how to bear and maintain the background environment, focusing on environmental containment and homogenization; the in-cabin wind tunnel layer is responsible for "how to establish and maintain local test airflow", focusing on aerodynamic loading; and the parameter adjustment layer is responsible for "how to generate, input, and dynamically compensate background environmental parameters", focusing on environmental supply and regulation. Only when these three layers—the parameter adjustment layer, the environmental cabin body layer, and the in-cabin wind tunnel layer—operate together can the in-cabin wind tunnel test system described in this invention for high-altitude aerodynamic coupling testing of aircraft components not only have an environment and airflow, but also continuously maintain the target high-altitude operating conditions throughout the entire test process.

[0225] The parameter adjustment layer includes a temperature control module (18), a pressure control module (19), a humidity control module (20), a check valve (17), a check valve (21), and an external clean gas input interface (28).

[0226] The parameter adjustment layer, through the temperature control module, pressure control module, and humidity control module, constitutes an upper-altitude parameter adjustment system. It performs "temperature-pressure-humidity" coordinated pretreatment on the gas entering the environmental chamber, and combines one-way valve (17) isolation and pre-balancing and slow-stop control strategies to achieve stable establishment and continuous maintenance of target upper-altitude environmental parameters. The parameter adjustment layer is composed of temperature control module (18), pressure control module (19), and humidity control module (20) working together to perform integrated pretreatment of temperature, pressure, and humidity on the working medium entering the upper-altitude environmental simulation chamber, thereby giving it the target upper-altitude environmental parameter state before it enters the chamber. Unlike environmental control devices that only adjust a single temperature, pressure, or humidity, the parameter adjustment layer does not perform post-processing of the chamber environment, but pre-processes the input medium through the coordinated adjustment of the three parameters of "temperature-pressure-humidity", making the establishment of the upper-altitude environmental background field more proactive, continuous, and controllable.

[0227] A one-way valve (17) is installed between the parameter regulation layer and the high-altitude environment simulation chamber to restrict the backflow of gas in the chamber to the inlet and outlet sides of the parameter regulation system. This forms a clear functional boundary in the system structure, suppresses the reverse disturbance of the low-pressure environment and internal circulation flow in the chamber on the parameter regulation unit, and ensures regulation accuracy and operational stability. The one-way valve (17) installed between the parameter regulation layer and the high-altitude environment simulation chamber is a key boundary management component for maintaining the stable operation of the entire test system. Under the conditions of low-pressure environment, continuous operation of the closed circulation wind tunnel in the chamber, and the combined effect of dynamic adjustment of multiple parameters, if there is no effective one-way isolation between the high-altitude environment simulation chamber and the parameter regulation subsystem, the gas in the chamber is prone to backflow or backflow along the parameter regulation path, which will cause disturbance of the inlet and outlet boundary conditions of the parameter regulation module, reduce the control accuracy of the temperature, pressure and humidity regulation process, and even cause system instability during the switching of operating conditions or the start-up and shutdown transient process. Based on this, the present invention implements directional constraints on the gas exchange path between the cabin or wind tunnel coupling system and the parameter adjustment subsystem by setting a one-way valve (17) between the parameter adjustment system of the parameter adjustment layer and the high-altitude environment simulation chamber. This blocks the reverse transmission of the low-pressure internal circulation flow field and transient disturbances in the cabin to the parameter adjustment unit, ensuring a clear and stable functional boundary between the background parameter supply side and the test load side. Thus, the one-way valve (17) is a key structural component for achieving system boundary isolation, maintaining parameter adjustment accuracy, and improving the stability of operating condition switching.

[0228] Meanwhile, the parameter regulation layer decouples the high-altitude environment setup process from the wind tunnel loading process by setting a pre-balancing phase (building the environment before starting the wind tunnel) and a slow-stop phase (reducing wind speed before withdrawing the environment), thereby reducing the impact of transient disturbances during start-up and shutdown on the effectiveness of the test. Specifically, the parameter regulation layer sets the pre-balancing and slow-stop phases according to the dynamic operating conditions in the high-altitude environment-wind tunnel coupled test process as follows: Before the test begins, the high-altitude parameter regulation system first adjusts the cabin air pressure, temperature, and humidity to the target values ​​and maintains them stably for a predetermined time before starting the cabin wind tunnel system to avoid interference from wind tunnel operation on the environment setup process; after the test, the wind tunnel airflow loading is first reduced and then shut down, and then the environmental regulation system is shut down with a delay to reduce the risks of pressure fluctuations, temperature and humidity drift, and condensation during shutdown.

[0229] The pre-balancing and slow-stop phases of the parameter adjustment layer described in this invention are process control logics proposed to address the dynamic coupling between high-altitude environmental parameter adjustment and the operation of the closed-loop wind tunnel. Under the combined effects of low pressure, low temperature, set humidity, and internal circulating airflow, the environmental setup process and the wind tunnel operation process are not independent of each other. If the wind tunnel is started before the internal environmental parameters have stabilized, the flow disturbances, pressure fluctuations, and thermal and moisture migration caused by the wind tunnel operation will inversely interfere with the background environmental setup, thereby affecting the accuracy of the target operating condition formation and the consistency of the test boundary conditions. Similarly, if environmental adjustment is removed before the wind tunnel has completed deceleration and unloading, it is easy to cause sudden pressure changes, temperature and humidity drift, and local condensation in the chamber during shutdown transients, thereby reducing the effectiveness and repeatability of the test results. The parameter adjustment layer described in this invention is a pre-balancing control strategy that establishes the environment first and then starts the wind tunnel, and a slow-stop control strategy that first reduces and removes the airflow loading and then delays the shutdown of the environmental adjustment system. This arrangement decouples the establishment of the high-altitude environmental background field from the loading of the local test flow field in time sequence, and ensures that the environmental removal and airflow unloading during the shutdown phase are completed in a controlled order, thereby reducing the unsteady-state effects caused by the mutual disturbance of multiple physics fields during system start-up and shutdown. Therefore, the pre-balancing and slow-down phases are not routine steps in the equipment operating procedures, but rather specialized methods designed for the dynamic behavior of high-altitude environment-wind tunnel coupled tests. This effectively improves the accuracy of target condition establishment, the stability of test boundary conditions, and the reliability of test results.

[0230] Therefore, the parameter adjustment layer can work in conjunction with the background parameter supply and process management platform of the closed high-altitude environment simulation chamber and the closed circulation wind tunnel inside the chamber, providing a guarantee for the entire test system to stably establish and maintain the target high-altitude environment under coupled conditions.

[0231] The parameter adjustment layer, the environmental cabin body layer, and the in-cabin wind tunnel layer are in a layered relationship: the environmental cabin body layer is responsible for how to bear and maintain the background environment, focusing on environmental containment and homogenization; the in-cabin wind tunnel layer is responsible for how to establish and maintain the local test airflow, focusing on aerodynamic loading; and the parameter adjustment layer is responsible for how to generate, input, and dynamically compensate for background environmental parameters, focusing on environmental supply and regulation. Only when these three layers—the parameter adjustment layer, the environmental cabin body layer, and the in-cabin wind tunnel layer—operate together can the in-cabin wind tunnel test system described in this invention for high-altitude aerodynamic coupling testing of aircraft components not only have an environment and airflow, but also continuously maintain the target high-altitude operating conditions throughout the entire test process.

[0232] Closed-loop control layer: coordinated operation of the environmental cabin body layer, the cabin wind tunnel layer, and the parameter adjustment layer.

[0233] The closed-loop control layer is responsible for establishing and maintaining the target high-altitude environmental parameters for the cabin, namely the generation and compensation of the three background field parameters of air pressure, temperature, and humidity. It organizes the originally coupled and mutually disturbing multi-physics field subsystems into a dynamic control center that can uniformly sense, judge, and regulate. The closed-loop control layer is used to implement cross-physics field linkage control of the wind tunnel system, high-altitude parameter regulation system, environmental homogenization structure, and anti-condensation unit based on multi-source feedback such as wind speed, pressure, temperature and humidity, and wall temperature, thereby achieving the overall stable maintenance of the high-altitude background environment, local test flow field, and system operation sequence.

[0234] The core task of the closed-loop control layer is to connect the environmental cabin body layer, the cabin wind tunnel layer, and the parameter adjustment layer into a system that coordinates real-time feedback, dynamic compensation, pre-balancing, and slow-down operation. Functionally, the closed-loop control layer primarily performs wind speed stability control, environmental consistency control, anti-condensation control, and full-process timing control. The wind speed stabilization control, based on feedback from the wind speed sensor in the test section and the pressure sensor inside the chamber, implements a linkage adjustment of the fan speed and the cross-sectional area of ​​the throat of the contraction section under low-pressure conditions to compensate for the impact of gas density changes on the target wind speed. The environmental consistency control, based on the spatial distribution information obtained by the temperature and humidity sensor array, triggers the dynamic operation of the intelligent environmental homogenization fan array when the temperature difference or humidity difference between any two points exceeds a set threshold, actively correcting the macroscopic temperature and humidity gradient inside the chamber. The anti-condensation control, based on the temperature and humidity state inside the chamber, calculates the dew point temperature in real time and compares it with the temperature of the wind tunnel shell wall. When there is a risk of condensation, it controls the start and stop of the electric heating film to avoid condensation from damaging the test boundary conditions and measurement effectiveness. The full-process timing control, which unifies the management of the three stages of pre-balancing, steady-state operation, and slow-stop reset, ensures that environmental setup, airflow loading, data acquisition, and shutdown unloading are completed in a controlled sequence, thereby reducing the impact of transient disturbances during start-up and shutdown on the test results.

[0235] The key to the closed-loop control layer is the establishment of a coupled closed-loop control logic that spans physical fields and functional levels. In the cabin wind tunnel test system for high-altitude aerodynamic coupling testing of aircraft components described in this invention, air pressure changes directly affect the wind speed in the test section, wind tunnel operation disturbs the spatial distribution of temperature and humidity inside the cabin, temperature and humidity conditions further determine the dew point location and condensation risk, and anti-condensation heating, in turn, alters the local thermal field distribution. Therefore, this invention addresses a typical multivariable, strongly coupled control problem. The role of the closed-loop control layer is to integrate the wind tunnel system, high-altitude parameter adjustment system, cabin sensing system, environmental homogenization structure, and anti-condensation unit into a unified scheduling framework using an industrial computer, comprehensively assessing multi-source state variables, and implementing coordinated control of multiple execution units to maintain the overall stability of the target operating condition.

[0236] The closed-loop control layer achieves unified coordination and dynamic stability maintenance of the high-altitude background environment, local test flow field, anti-condensation state, and the entire process operation sequence by constructing a cross-physics field coupling based on multi-source feedback of wind speed, air pressure, temperature and humidity, and wall temperature. The closed-loop control layer constitutes a multi-variable coordinated control hub for high-altitude environment-aerodynamic load coupled test conditions, used to uniformly perceive, judge, and regulate the mutually coupled and disturbed multi-physics field processes within the system. Specifically, the closed-loop control layer uses an industrial computer as its core, comprehensively integrating multi-source state variables such as wind speed, air pressure, temperature and humidity, and wall temperature. It unifies the high-altitude parameter adjustment system, the closed-loop wind tunnel inside the cabin, the environmental homogenization structure, and the anti-condensation unit into a single scheduling framework, thereby breaking through the traditional decentralized mode of independent closed-loop control of temperature, pressure, humidity, and wind speed.

[0237] Given that low-pressure changes directly affect the wind speed in the test section, wind tunnel operation will inversely disturb the spatial distribution of temperature and humidity inside the chamber, and the temperature and humidity state determines the dew point location and condensation risk, while anti-condensation heating further affects the local thermal field distribution, the present invention is essentially a multivariable dynamic control problem with obvious cross-coupling characteristics. To address this, the closed-loop control layer employs two mechanisms. First, it uses feedback from the wind speed sensor in the test section and the pressure sensor inside the chamber to adjust the wind tunnel fan speed and the cross-sectional area of ​​the throat in the contraction section, compensating for wind speed attenuation under low-density medium conditions. Second, based on spatial distribution information obtained from the temperature and humidity sensor array, it controls the dynamic operation of the intelligent environmental homogenizing fan array when the temperature or humidity difference between any two points exceeds a set threshold, reducing the macroscopic temperature and humidity gradient inside the chamber and maintaining background environmental consistency. Simultaneously, it calculates the dew point temperature based on the temperature and humidity conditions inside the chamber and assesses the condensation risk by combining it with the wind tunnel shell wall temperature, thereby controlling the start and stop of the electric heating film to prevent condensation from interfering with the test boundary conditions and measurement results. Furthermore, it implements time-series management for the entire process of pre-balancing, steady-state operation, and slow-stop reset, ensuring that environmental setup, airflow loading, data acquisition, and shutdown unloading are completed in a controlled sequence. Therefore, the closed-loop control layer is the core control layer used to coordinate the stable operation of the background environmental field, local test flow field, thermal and humidity conditions, and structural boundary conditions, thereby ensuring that the entire platform can maintain the stability, consistency, and repeatability of the target test state even under complex coupled operating conditions.

[0238] The difficulty in establishing a closed-loop control layer lies in the fact that the essence of high-altitude environment coupling tests is not single-parameter control, but rather the linkage control between the background field, test field, thermal and humidity conditions, and structural boundaries. In particular, the introduction of dew point criteria into anti-condensation decision-making, the use of spatial uniformity of temperature and humidity inside the chamber as an independent control objective, and the simultaneous inclusion of the test local flow field and the background environment inside the chamber into a unified closed loop indicate that the closed-loop control layer is no longer ordinary equipment automation, but a multivariable coordinated control system specifically designed for high-altitude environment-wind tunnel coupling conditions.

[0239] The closed-loop control layer includes an industrial computer (23), a data acquisition card (31), a wind tunnel pressure sensor (15), a temperature and humidity sensor array (2), a wind tunnel wind speed sensor (9), a wind tunnel wall temperature sensor (5), a UWB wireless communication interface (29), an external clean gas input interface (28), and control interfaces (30) for the fan, the contraction section servo mechanism, the parameter adjustment module, the electric heating film, and the homogenizing fan array.

[0240] In the closed-loop control layer, the industrial computer (23) is connected to the wind tunnel system, parameter adjustment system and cabin sensing system to form a unified scheduling platform; multi-source sensor feedback, including wind speed, pressure, temperature and humidity, and wall temperature; bidirectional coupling dynamic control is cross-module linkage; pre-balance-steady-state operation-gradual stop and reset full-process control forms a complete test sequence control.

[0241] Firstly, the closed-loop control layer forms a cross-physical field coupled closed loop. Employing this cross-physical field coupled closed-loop control method, it incorporates air pressure, wind speed, temperature and humidity, and wall thermal state into a unified control framework. This overcomes the difficulty of handling mutual disturbances in traditional multi-parameter independent loop control, achieving coordinated and stable control of the high-altitude environmental background field and the local experimental flow field. The closed-loop control layer constructs a multivariable dynamic closed-loop control mechanism coupled across physical fields. Under the condition of the high-altitude environmental simulation chamber and the enclosed circulating wind tunnel operating together, there are no independent relationships between the controlled variables. Changes in air pressure within the chamber directly alter the working medium density and affect the establishment of wind speed in the test section. Flow disturbances caused by wind tunnel operation change the spatial uniformity of temperature and humidity within the chamber. Changes in temperature and humidity further determine the dew point temperature and affect the risk of condensation, while the anti-condensation heating process has a reverse effect on the local thermal field distribution. Therefore, this invention addresses the multivariable coordinated control problem of the coupling between the background environmental field, the local experimental flow field, the thermal and humidity state, and the structural wall state. Based on this, the closed-loop control layer implements coordinated regulation of the wind tunnel system, high-altitude parameter adjustment system, environmental homogenization structure, and anti-condensation unit through a unified control center. This ensures that wind speed maintenance, environmental uniformity maintenance, and condensation risk suppression are no longer isolated local functions, but are comprehensively judged and executed collaboratively within the same control framework. Therefore, the closed-loop control layer is a cross-physics field coupled closed-loop control system constructed for the coupled high-altitude environment-wind tunnel operating conditions, enabling the overall stability maintenance of the platform's target operating conditions under complex disturbance conditions.

[0242] Secondly, in the closed-loop control layer, the threshold-triggered environmental homogenization logic embodies the hierarchical control of the background field and the test field. By setting threshold-triggered environmental homogenization logic, the closed-loop control layer treats the homogenization of the background environmental field within the cabin as an independent control objective, combining it with the local flow field control in the test section to achieve hierarchical closed-loop coordinated control of the background field and the test field. The environmental homogenization control of the closed-loop control layer does not solely rely on the test section wind speed reaching a set value as the only control objective; rather, it further incorporates the spatial consistency of the background environmental field within the high-altitude environment simulation cabin into an independent controlled object, thus forming a hierarchical coordinated closed-loop control mechanism of "test local field – cabin background field." The fact that the local inflow in the test section meets the target wind speed does not necessarily mean that the entire test environment is effective; if there is a significant spatial unevenness in the temperature and humidity distribution within the cabin, it will not only affect the stability of sensor measurements and the consistency of material loading, but also change local dew point conditions, exacerbate the risk of condensation, and cause the boundary conditions around the specimen to deviate from the actual high-altitude service state. Therefore, the closed-loop control layer's environmental homogenization control monitors environmental parameters at different locations within the chamber in real time using a temperature and humidity sensor array. When the temperature or humidity difference between any two points exceeds a preset threshold, it triggers the dynamic operation of an intelligent environmental homogenization fan array to actively correct the macroscopic temperature and humidity gradient within the chamber. Thus, the control logic not only focuses on the local flow field quality of the test section but also simultaneously considers the consistency of the overall background environment within the chamber, ensuring that both the local test field and the background field are included in a unified closed-loop control range. This guarantees the authenticity of the boundary conditions, the validity of the measurements, and the repeatability of the test results. This technical approach, which integrates local test flow field control and chamber background environment homogenization control into a closed-loop system in parallel, differs from methods that only target the wind speed in the test section for single-objective control.

[0243] The closed-loop control layer is integrated with the environmental cabin body layer, the cabin wind tunnel layer, and the parameter adjustment layer. The closed-loop control layer is responsible for the coupling coordination and dynamic stability maintenance of the entire system. The environmental cabin body layer addresses the bearing and homogenization of the high-altitude background environment, ensuring "background field stability." The cabin wind tunnel layer addresses the establishment of local test airflow and the maintenance of flow field quality, ensuring "test flow success." The parameter adjustment layer addresses the generation, input, and compensation of high-altitude background parameters, ensuring "target operating conditions are met." The closed-loop control layer addresses how to ensure that the above three layers do not conflict with each other in the same space and time, and that they can still work collaboratively according to the target operating conditions even in the presence of disturbances. It is responsible for "stable, coordinated, and continuous operation of the environmental cabin body layer, cabin wind tunnel layer, and parameter adjustment layer." The first three layers answer "what constitutes the system and what does each layer do," while the closed-loop control layer answers "how the system operates stably." The closed-loop control layer is not a controller attached to a single module, but rather the operational center and coupling coordination core of the entire platform.

[0244] Structurally, the in-cabin wind tunnel test system for high-altitude aerodynamic coupling testing of aircraft components described in this invention is divided into a high-altitude environment simulation cabin, an in-cabin environment homogenization component, an in-cabin enclosed wind tunnel test system, a high-altitude parameter adjustment system, and a measurement and execution component.

[0245] High-altitude environment simulation chamber: provides physical space and basic environmental boundaries

[0246] The high-altitude environment simulation chamber, as the basic supporting unit of the entire wind tunnel test system, provides the basic conditions required for establishing a sealed physical space boundary and a high-altitude environmental background. The high-altitude environment simulation chamber not only serves as the installation carrier for the wind tunnel test system, environmental monitoring unit, and auxiliary execution structure, but also as the spatial boundary maintenance unit of the entire test platform, providing the basic conditions for the controllable establishment and stable maintenance of environmental parameters such as air pressure, temperature, and humidity inside the chamber. The high-altitude environment simulation chamber constitutes the "container layer" of the test system of this invention, determining the spatial enclosure, environmental controllability, and the prerequisite for the coordinated operation of the various subsystems within the entire platform.

[0247] The high-altitude environment simulation chamber mainly consists of an environment chamber body (22) and an environment chamber body insulation layer (1). The environment chamber body (22) is used to form a sealed volume that is isolated from the outside world, so as to limit the leakage of gas inside the chamber and maintain the stable existence of a low-pressure environment. The environment chamber body insulation layer (1) is used to weaken the heat exchange between the inside and outside of the chamber, reduce the disturbance of external environmental fluctuations on the temperature field inside the chamber, thereby improving the ability to maintain the environmental parameters inside the chamber under low-temperature conditions.

[0248] Interior environment homogenization components: maintain uniform temperature and humidity inside the cabin.

[0249] The cabin environment homogenization component, as an active homogenization unit for the background environmental field inside the high-altitude environment simulation chamber, is used to maintain the consistency of the spatial distribution of temperature and humidity parameters inside the chamber, thereby suppressing the interference of local environmental distortion on the test results. The cabin environment homogenization component is not used as a power source for forming the airflow in the test section, but rather to maintain the thermal and humidity balance of the overall background environment inside the high-altitude environment simulation chamber, improve the uniformity and stability of the temperature and humidity field inside the chamber, and thus ensure the consistency and reliability of the test boundary conditions, flow field state, and parameter measurement results. The cabin environment homogenization component constitutes the background field homogenization layer of the test system of this invention, and its core purpose is to ensure the uniform distribution of the overall environmental field inside the chamber and prevent local thermal and humidity disturbances from causing additional effects on aerodynamic tests and environmental response tests.

[0250] The cabin environment homogenization component mainly consists of an intelligent environment homogenization fan array 1 (3), an intelligent environment homogenization fan array 2 (16), and a cabin temperature and humidity sensor array (2). The cabin temperature and humidity sensor array (2) is used to collect temperature and humidity data at different locations in the high-altitude environment simulation cabin in real time to obtain spatial distribution information of cabin environmental parameters. The intelligent environment homogenization fan array 1 (3) and the intelligent environment homogenization fan array 2 (16) dynamically adjust the start-stop state or operating speed according to the data fed back by the temperature and humidity sensor array, and actively reduce and homogenize the temperature and humidity gradient caused by wind tunnel operation, specimen arrangement, or local heat and mass exchange.

[0251] Enclosed wind tunnel testing system: generates controllable test airflow.

[0252] The enclosed wind tunnel test system, as the core unit for flow field generation of the entire platform, is used to form a stable, controllable test airflow with good flow field quality under the low pressure, low temperature and set humidity background conditions established in the high-altitude environment simulation chamber, thereby providing high-fidelity aerodynamic loads for the aircraft components under test. The enclosed wind tunnel test system constitutes the "flow field generation layer" or "experimental core layer" of the test platform of this invention, directly acting on the model under test, and is responsible for generating aerodynamic loads with high stability, high uniformity and high reliability. It is a key technology for realizing the high-altitude performance verification of aircraft components.

[0253] The main components of the enclosed wind tunnel test system include a wind tunnel fan (6), an adjustable shrink section (7), a rectifier 1 (8), a test section (11), a wind tunnel shell (24), an anti-condensation electric heating film (4), a wind tunnel wall temperature sensor (5), a wind tunnel wind speed sensor (9), a wind tunnel gas temperature sensor (13), a wind tunnel humidity sensor (14), and a wind tunnel pressure sensor (15). Among them, the wind tunnel fan (6) is used to drive the working medium to form a closed loop flow in the wind tunnel shell; the adjustable contraction section (7) is used to adjust the local flow acceleration capability by changing the throat cross-sectional area, and works with the wind tunnel fan (6) to form a wind speed closed loop adjustment unit to compensate for the wind speed attenuation caused by the decrease in gas density under low air pressure conditions, and ensure the stable establishment and continuous maintenance of the target wind speed in the test section; the rectifier 1 (8) adopts a honeycomb guide structure and a multi-layer metal wire mesh composite arrangement to weaken large-scale disturbances and small velocity pulsations, reduce the turbulence of the test section (11) and improve the uniformity of flow velocity distribution, thereby improving the stability and repeatability of the test flow field; the test section (11) is the area where the test object is arranged, and directly bears the test flow generated by the wind tunnel system; the wind tunnel wind speed sensor (9) is used to detect the actual wind speed of the test section (11) in real time, and provide feedback basis for the linkage adjustment of the wind tunnel fan (6) and the adjustable contraction section (7).

[0254] Furthermore, considering the risk of condensation in the wind tunnel shell and adjacent areas of the test section under low temperature, high humidity, and closed internal circulation conditions, this invention provides an anti-condensation electric heating film (4) on the outer wall of the wind tunnel shell (24), and combines it with a wind tunnel wall temperature sensor (5) to monitor the shell wall temperature in real time, so as to implement targeted heating protection when condensation tends to occur, and prevent condensation from interfering with the flow field surface state, the test specimen load conditions, and the test results. Thus, the enclosed wind tunnel test system described is not a simple arrangement of ordinary wind tunnel devices in an environmental chamber, but a special flow field generation system that takes into account wind speed establishment, flow field rectification, accurate measurement, and anti-condensation protection under high-altitude low-density conditions.

[0255] Upper-altitude parameter regulation system: generates and maintains target upper-altitude environmental parameters

[0256] The high-altitude parameter adjustment system, as the environment generation and supply unit of the entire platform, is used to generate and continuously maintain the target high-altitude environmental parameters required for the test, thereby providing stable, controllable and repeatable background boundary conditions for the high-altitude environment simulation chamber and the enclosed wind tunnel test system inside the chamber. The high-altitude parameter adjustment system constitutes the "background parameter generation layer" or "environment generation and supply layer" of the test platform of this invention. Its core function is to provide correct, stable and repeatable temperature, pressure and humidity boundary conditions for the wind tunnel system and the test environment inside the chamber, thereby ensuring that the flow field state and environmental parameters are controllable and reproducible throughout the test process.

[0257] The high-altitude parameter adjustment system mainly comprises a temperature control module (18), a pressure control module (19), a humidity control module (20), a one-way valve (17), and a one-way valve (21). The temperature control module (18) regulates the temperature of the working medium entering the chamber to establish and maintain the target low temperature or set temperature conditions. The pressure control module (19) adjusts the absolute pressure level inside the chamber to create a low-pressure environment corresponding to the target altitude. The humidity control module (20) controls the humidity of the working medium to establish the set relative humidity conditions. These three modules are not independent single-function adjustment units, but rather work collaboratively to regulate the temperature, pressure, and humidity of the gas entering the high-altitude environment simulation chamber. This ensures that the background environmental parameters reach the target state at the input stage, thereby improving the initiative, accuracy, and continuity of the chamber environment establishment process.

[0258] Furthermore, the one-way valve (17) and one-way valve (21) are located between the high-altitude parameter adjustment system and the high-altitude environment simulation chamber to ensure that the gas flows unidirectionally in a predetermined direction, preventing the gas inside the chamber from flowing back or flowing back to the parameter adjustment side under low pressure and internal circulation conditions. This avoids disturbance to the boundary conditions at the inlet and outlet of the adjustment module, ensuring the accuracy of parameter adjustment and the stability of system operation. Thus, the high-altitude parameter adjustment system not only undertakes the function of generating background environmental parameters, but also undertakes the boundary management function between the high-altitude environment supply side and the coupling side of the chamber or wind tunnel.

[0259] Measurement and execution components: enable system linkage, closed-loop control, and data acquisition.

[0260] The measurement and execution component, serving as the intelligent control and data acquisition unit of the entire platform, is used to achieve linkage control, closed-loop adjustment, and test data acquisition between the high-altitude environment simulation chamber, the enclosed wind tunnel test system, and the high-altitude parameter adjustment system. This ensures the stable operation and high-fidelity measurement of high-altitude environmental parameters and test flow fields under coupled conditions. The measurement and execution component is not a single data recording module or local actuator, but rather an "intelligent control and data layer" that runs through all the aforementioned hierarchical structures of this invention. Its core function is to connect the various stages of environment generation, background homogenization, flow field establishment, and specimen loading, thereby achieving the coordinated and stable maintenance of high-altitude environmental parameters and aerodynamic load conditions, and simultaneously acquiring in-chamber environmental data and aerodynamic response data, providing a reliable basis for the high-altitude performance verification of aircraft components.

[0261] The measurement and execution component mainly consists of an industrial computer (23), a fully built-in wireless measurement and control support rod (25), a six-dimensional force measurement unit (26), an attitude adjustment mechanism (27), an external clean gas input interface (28), a UWB wireless communication interface (29), a data acquisition card (31), and a control interface (30) connected to the fan, the contraction section servo mechanism, the parameter adjustment module, the electric heating film, and the homogenizing fan array.

[0262] Among them, the fully built-in wireless measurement and control support rod (25) is used to carry the test piece and complete the attitude adjustment and measurement signal transmission, avoiding the damage of the system sealing and the stability of the cabin environment to the through-cabin cable; the attitude adjustment mechanism is used to realize the precise adjustment of the angle of attack or installation attitude of the test piece; the six-dimensional force measurement unit (26) is used to acquire the aerodynamic load information such as lift, drag, lateral force and torque of the test piece during the test; the UWB wireless communication interface (29) is used to realize the wireless transmission of measurement data and control commands.

[0263] Specifically, the bidirectional coupled environmental dynamic control system takes an industrial computer (23) and a data acquisition card (31) as its core, collects, judges and adjusts multiple sources of signals such as wind speed, air pressure, temperature, humidity and wall thermal state in a unified manner, and automatically controls the wind tunnel fan, adjustable contraction section, environmental homogenization fan array and electric heating film based on the feedback results, thereby forming a coupled closed-loop control of multiple physical field parameters.

[0264] Cascaded Control Architecture Based on Feedforward Compensation: Two-Way Coupled Environmental Dynamic Control System (23)

[0265] The bidirectional coupled environmental dynamic control system (23) does not operate wind speed control, air pressure control, temperature control, humidity control and environmental uniformity control separately in isolation. Instead, it adopts a cascaded control architecture based on feedforward compensation, so that the wind speed control in the wind tunnel test section and the control of the environmental parameters inside the cabin work together under the same control framework.

[0266] The bidirectional coupled environmental dynamic control system (23) organizes subsystems with different response speeds and different control objectives in layers: the wind speed of the test section, which changes rapidly and is most sensitive to the test results, is the priority control object of the inner loop; the uniformity of the cabin environment, which changes slowly but affects the overall test boundary conditions, is the adjustment object of the outer loop; and the gas density change caused by changes in air pressure and temperature is directly applied to the fan speed and the throat area of ​​the contraction section through feedforward compensation to reduce the impact of disturbances on the wind speed closed loop.

[0267] The core purpose of the bidirectional coupled environmental dynamic control system (23) is to enable the wind speed in the test section to quickly track the set value during the continuous adjustment of chamber pressure, temperature and humidity, while suppressing the impact of uneven local temperature and humidity in the chamber on the wind tunnel flow field and test reliability, thereby achieving high-precision decoupling and coordinated control between wind speed and environmental parameters.

[0268] The bidirectional coupled environmental dynamic control system (23) adopts a cascaded control architecture based on feedforward compensation to achieve high-precision decoupling and coordinated control of wind speed and environmental parameters. Its control structure and variable definitions are as follows:

[0269] Firstly, the control variable and the controlled object:

[0270] Controlled variables: actual wind speed V, cabin air pressure P, temperature T, relative humidity RH in test section (11), and cabin space environment uniformity index (temperature difference ΔT and humidity difference ΔRH between any two points).

[0271] Controlled quantities: the rotational speed n of the wind tunnel fan (6), the throat cross-sectional area At of the contraction section (7), the output of the temperature control module (18), the output of the pressure control module (19), the output of the humidity control module (20), the rotational speed of the intelligent environmental homogenizing fan array (3, 16), and the heating power of the anti-condensation electric heating film (4).

[0272] Key disturbances include: changes in cabin pressure P caused by the operation of the pressure control module (which in turn changes the gas density ρ), local temperature and humidity gradients caused by the turbulence of the test model itself, and potential disturbances to the wind tunnel flow field when the environmental control system (temperature control and humidity control) is activated.

[0273] Secondly, the control structure of cascaded + feedforward compensation:

[0274] Inner loop: Fast wind speed closed loop. The wind speed Vact is collected in real time by the wind speed sensor in the test section (11), and compared with the target wind speed V∗. The fan speed n is adjusted by the high-speed PID controller (sampling frequency 200Hz, using IIR low-pass filter) to achieve fast wind speed tracking.

[0275] Feedforward: Density Change Compensation. When the cabin pressure P or temperature T changes, the system calculates the gas density ρ(P,T) in real time. To maintain a constant dynamic pressure q = 1 / 2ρV² or volumetric flow rate, the system employs a feedforward compensation strategy, synchronously adjusting the fan speed n and throat area At. Its engineering compensation rules are as follows:

[0276] To maintain the target wind speed V∗, the volumetric flow rate Q = V⋅At ​​needs to be kept stable. Since the fan speed n is approximately proportional to the volumetric flow rate, when the gas density ρ decreases (e.g., due to a drop in air pressure), the following must be executed simultaneously:

[0277] n = n0⋅f(ρ0 / ρ) (Increase the rotational speed)

[0278] At = At0⋅f(ρ / ρ0) (Reduce throat area)

[0279] Where f is a monotonic compensation function obtained from system calibration, preferably a linear function, a piecewise linear function, or a lookup table function;

[0280] Where n0 and At0 are the initial values ​​under standard density ρ0. To avoid system oscillations caused by abrupt changes in the control quantity, the rates of change of n and At are limited:

[0281] |dn / dt|≤500rpm / s (slope limit)

[0282] |dAt / dt|≤10%At max / s (slope constraint)

[0283] Outer loop: Environmental uniformity closed loop. Multiple points ΔT and ΔRH are monitored by a temperature and humidity sensor array (2). When the deviation exceeds the set threshold (ΔT>1℃ or ΔRH>5%), the outer loop controller (sampling frequency 2Hz) outputs a control signal to adjust the speed of the intelligent environmental homogenization fan array (3, 16) until uniformity is restored. To avoid frequent fan start-stop, a hysteresis interval (ΔT<0.5℃ and ΔRH<3% and exits after 60 seconds) and a minimum running time (120 seconds) are set.

[0284] Wind speed inner loop (high speed): sampling frequency 200 Hz, using a second-order IIR low-pass filter (cutoff frequency 20 Hz), after filtering out high-frequency noise, the fan speed n is output by the high-speed PID controller.

[0285] Density compensation feedforward (event triggered): Each time the data from the chamber pressure sensor or chamber temperature sensor is updated (update frequency ≥ 10 Hz), the system immediately recalculates the gas density ρ(P,T) and updates the feedforward target values ​​of the fan speed n and throat area At according to the preset compensation rules.

[0286] Uniformity outer loop (low speed): Sampling frequency of 2 Hz, used to drive the intelligent environmental homogenization fan array (3, 16). The slower sampling frequency, combined with a larger filter window, avoids unnecessary fan responses to small, instantaneous temperature and humidity fluctuations, reducing mechanical wear and airflow disturbances.

[0287] Furthermore, the two-way coupled environmental dynamic control system includes the coupling of environmental parameters to wind speed control and the coupling of wind tunnel operation to environmental distribution.

[0288] The coupling of environmental parameters with wind speed control: Changes in air pressure P and temperature T alter gas density ρ, thereby affecting the fan operating point, flow rate, and wind speed in the test section. Therefore, the actions of the environmental system will influence the wind speed system.

[0289] The coupling of wind tunnel operation with environmental distribution: The operation of the wind tunnel fan, model turbulence, and high-speed airflow passing through the test section alter the local flow and heat transfer conditions within the chamber, thereby affecting the uniformity of temperature and humidity distribution. Therefore, the operation of the wind tunnel system, in turn, affects the environmental system.

[0290] Because of this dual effect, the system cannot simply separate wind speed control and environmental control. Instead, it must form a unified control framework through inner loop wind speed closed-loop, density change feedforward compensation, outer loop environmental uniformity closed-loop, and anti-condensation local thermal control.

[0291] The bidirectional coupled environmental dynamic control system (23) adopts a cascaded control architecture based on feedforward compensation to achieve high-precision decoupling and coordinated control of wind speed in the test section and environmental parameters inside the chamber. Specifically, the actual wind speed V in the test section, air pressure P inside the chamber, temperature T, relative humidity RH, and environmental uniformity index T and ARH inside the chamber are the main controlled variables; the wind tunnel fan speed n, the throat cross-sectional area A of the contraction section (7), the output of the temperature control module (18), the output of the pressure control module (19), the output of the humidity control module (20), the speed of the intelligent environmental homogenization fan array (3,16), and the heating power of the anti-condensation electric heating film (4) are the main control variables. The control system uses the inner loop wind speed closed loop as the fast control link. The wind speed sensor in the test section (11) collects the actual wind speed Vact in real time and compares it with the target wind speed V. The high-speed PID controller outputs the fan speed adjustment command. At the same time, when the air pressure P or temperature T in the cabin changes and causes the gas density p to change, the control system performs feedforward compensation on the fan speed n and throat area A according to the preset compensation function. When the gas density decreases, the fan speed is increased and the throat area is reduced to compensate for the wind speed attenuation under low density conditions. In order to prevent the system oscillation caused by the sudden change of the actuator, the rate of change of the fan speed and throat area adjustment is limited. The control system also sets an environmental uniformity outer loop. The temperature and humidity sensor array (2) monitors the temperature difference T and humidity difference RH at multiple points in the cabin. When they exceed the set threshold, the outer loop controller outputs the control signal to adjust the speed of the intelligent environmental homogenization fan array (3, 16) to restore the environmental uniformity in the cabin. The hysteresis interval and minimum running time limit are used to avoid frequent start and stop of the fan. Therefore, wind speed control, density compensation, environmental homogenization, and anti-condensation control are incorporated into the same control architecture to achieve stable test control under high-altitude multi-parameter coupled conditions.

[0292] In terms of connectivity, the in-cabin wind tunnel test system for high-altitude aerodynamic coupling testing of aircraft components described in this invention is divided into mechanical-installation connection, fluid connection, and electrical signal connection.

[0293] Mechanical-installation connection:

[0294] In the in-cabin wind tunnel test system for high-altitude aerodynamic coupling testing of aircraft components described in this invention, each functional unit is mechanically integrated and installed within the cabin, as detailed below:

[0295] The enclosed wind tunnel test system is located inside the high-altitude environment simulation chamber and is integrated with the environment chamber as a core functional component.

[0296] Specifically, the wind tunnel fan (6), the contraction section (7), the rectifier (8), and the test section (11) are connected sequentially along the airflow direction to form a closed wind tunnel loop set inside the high-altitude environment simulation chamber, so that the test airflow forms an independent circulation inside the chamber without direct exchange with the outside. The anti-condensation electric heating film (4) is attached to the outer wall of the wind tunnel shell to provide local heating protection for the wind tunnel shell and the adjacent area of ​​the test section. The intelligent environmental homogenization fan array (3, 16) is installed in the upper and lower areas of the inner wall of the high-altitude environment simulation chamber to form an upper and lower partitioned homogenization arrangement facing the overall background environment field inside the chamber. The temperature and humidity sensor array (2) is fixedly set in different positions inside the chamber to obtain the spatial distribution information of environmental parameters at multiple points inside the chamber. The test piece (10) is installed inside the test section (11) through a fully built-in wireless measurement and control support rod (25). The fully built-in wireless measurement and control support rod (25) is used to support the test piece and to realize the wireless transmission of the test piece attitude adjustment and related measurement signals.

[0297] Therefore, the in-cabin wind tunnel test system for high-altitude aerodynamic coupling testing of aircraft components described in this invention, through the above-mentioned mechanical installation connection relationship, enables the environmental cabin, wind tunnel, environmental homogenization component, sensor component and specimen support and control component to form a compact and functionally distinct integrated installation system in the same sealed space, providing a mechanical foundation for the coupling construction and stable operation of high-altitude environment and test flow field.

[0298] Fluid connection:

[0299] In the in-cabin wind tunnel test system for high-altitude aerodynamic coupling testing of aircraft components described in this invention, each functional unit forms a layered fluid connection relationship in the fluid pathway: "external air source pretreatment—environmental cabin background establishment—in-cabin wind tunnel closed loop," as detailed below:

[0300] Specifically, external clean gas first enters the high-altitude parameter regulation system, and then undergoes temperature, pressure, and humidity pretreatment sequentially through the temperature control module (18), pressure control module (19), and humidity control module (20), ensuring that the working medium entering the system reaches the preset high-altitude environmental parameter state before entering the high-altitude environment simulation chamber. The gas, after the above pretreatment, then enters the environment chamber through a one-way valve located between the high-altitude parameter regulation system and the high-altitude environment simulation chamber, thereby establishing a background environment with target temperature, pressure, and humidity within the high-altitude environment simulation chamber.

[0301] Specifically, the enclosed wind tunnel test system is set up inside the high-altitude environment simulation chamber, forming an independent closed-loop airflow circuit within this background environment. The working medium within the wind tunnel circuit does not directly exchange with the outside environment, but continuously circulates under the established temperature, pressure, and humidity conditions inside the chamber, thereby ensuring that the test airflow is always within the target high-altitude environmental boundary conditions. At the same time, the one-way valve (21) is used to restrict the reverse flow of gas inside the environmental chamber towards the high-altitude parameter adjustment system, preventing backflow interference from the low pressure and internal circulation conditions inside the chamber on the parameter adjustment side.

[0302] Therefore, through the above-mentioned fluid connection relationship, the present invention realizes the organic connection between the background environment generation path and the test airflow circulation path in the cabin, so that the high-altitude environmental parameters can be stably input and maintained in the cabin, while the wind tunnel test airflow can circulate independently without damaging the background environment in the cabin, thereby providing stable and controllable fluid boundary conditions for the high-altitude performance testing of aircraft components.

[0303] Electrical signal connection:

[0304] In the cabin wind tunnel test system for high-altitude aerodynamic coupling testing of aircraft components described in this invention, each functional unit forms a unified monitoring-control network in terms of electrical connection and signal transmission. Among them, the industrial computer (23) serves as the core control node of the bidirectional coupled environment dynamic control system and is electrically connected to various sensors and actuators in the cabin.

[0305] Specifically, the industrial computer (23) receives status signals collected by the temperature and humidity sensor array, air pressure sensor, wind speed sensor and wall temperature sensor through the data acquisition interface, and uses them to acquire key parameters such as temperature, humidity, air pressure, wind speed of the test section and wall temperature of the wind tunnel shell in real time. At the same time, the industrial computer (23) is connected to the wind tunnel fan (6), the contraction section servo mechanism, the temperature control module (18), the pressure control module (19), the humidity control module (20), the electric heating film (4) and the homogenizing fan array (3, 16) through the control interface, and uses them to implement linkage adjustment of each execution unit based on the real-time acquired data, so as to realize unified control of functions such as wind speed maintenance, environmental parameter establishment, background field homogenization and anti-condensation protection.

[0306] Specifically, the wireless measurement and control support rod installed inside the test section interacts with the industrial computer (23) via the UWB wireless communication protocol to exchange data and control commands. This eliminates the need for transmission of specimen attitude adjustment signals and measurement data through the cabin cable, thereby avoiding the damage to the airtightness and internal environmental stability of the high-altitude environment simulation chamber caused by traditional wired connections. Thus, this invention organically integrates environmental monitoring, execution control, and specimen measurement through the aforementioned electrical and signal connections. This enables the high-altitude environment simulation chamber, the enclosed wind tunnel test system, the high-altitude parameter adjustment system, and the specimen measurement and control unit to operate collaboratively under a unified control framework, providing the electrical and signal foundation for the multi-physics closed-loop control and high-fidelity data acquisition of the entire platform.

[0307] From the perspective of coupling chain relationships, the in-cabin wind tunnel test system for high-altitude aerodynamic coupling testing of aircraft components described in this invention mainly illustrates the environmental establishment coupling chain, the sealing and measurement coupling chain, and the pre-balancing-steady-state control-deceleration coupling chain. Furthermore, the wind speed establishment coupling chain, the flow field quality coupling chain, and the flow field quality coupling chain are described in the divisional patent.

[0308] Establishing a coupling chain in the environment:

[0309] In the in-cabin wind tunnel test system for high-altitude aerodynamic coupling testing of aircraft components described in this invention, the establishment and maintenance of the target high-altitude environment are achieved through an environment establishment coupling chain.

[0310] Specifically, the temperature control module (18), pressure control module (19), and humidity control module (20) work together to regulate the temperature, pressure, and humidity of the working medium entering the system in an integrated manner, and input it into the high-altitude environment simulation chamber through a one-way valve, thereby providing the chamber with an environmental medium that meets the target working conditions at the source. The gas entering the environment chamber is contained in the sealed space formed by the chamber body (22), and the heat exchange and environmental disturbance between the gas and the outside world are reduced by the heat insulation effect of the insulation layer (1), so as to maintain the overall stability of the temperature, pressure, and humidity boundaries inside the chamber.

[0311] Meanwhile, the temperature and humidity sensor array (2) performs multi-point real-time detection of the temperature and humidity status at different locations in the chamber to obtain spatial distribution information of environmental parameters; when a temperature or humidity deviation is detected in a local area, the intelligent environmental homogenizing fan array 1 (3) and the intelligent environmental homogenizing fan array 2 (16) operate under the scheduling of the control system to actively reduce and homogenize the macro temperature and humidity gradient in the chamber, thereby suppressing the adverse effects of local environmental heterogeneity on the experimental boundary conditions.

[0312] Thus, each unit forms a complete coupled link from target environmental parameter generation, cabin input, boundary maintenance, state perception to active homogenization correction, realizing the stable establishment of high-altitude environmental parameters and the maintenance of spatial uniformity.

[0313] Sealing and measurement coupling chain:

[0314] In the in-cabin wind tunnel test system for high-altitude aerodynamic coupling testing of aircraft components described in this invention, the compatibility between system sealing and high-precision measurement of the test specimen is achieved through a sealing and measurement coupling chain. Considering that the high-altitude environment simulation chamber has high requirements for sealing performance under low-pressure conditions, and that traditional test schemes often require additional through-cabin cables and interfaces as the number of measurement items increases, which can easily lead to increased risk of cabin leakage, distortion of boundary conditions, and decreased measurement reliability, this invention adopts a fully built-in wireless measurement and control support rod (25) as the test specimen support and measurement execution unit.

[0315] The fully built-in wireless measurement and control support rod (25) is installed inside the test section (11) to complete the mechanical support, attitude adjustment and six-dimensional force signal acquisition of the test component (10), and to interact with the external control system through the wireless communication protocol, thereby avoiding the transmission of a large number of measurement signals and control signals through the cabin cable. As a result, while reducing the number of cabin penetration interfaces, the risk of leakage in the high-altitude environment simulation cabin under low-pressure conditions is reduced.

[0316] Furthermore, the fully integrated wireless measurement and control support rod (25), together with the isolation structure of the one-way valve 1 (17) or one-way valve (21) and the enclosed wind tunnel circuit inside the cabin, enable the high-altitude environment simulation cabin to achieve high-precision measurement of the specimen's attitude and aerodynamic response while maintaining sealed boundary conditions. Thus, the above-mentioned units form a coupling link that balances sealing performance and measurement accuracy, enabling the present invention to complete high-fidelity test data acquisition without compromising the stability of the high-altitude cabin environment.

[0317] This invention achieves specimen support, attitude adjustment and six-dimensional force acquisition through a fully built-in wireless measurement and control support rod (25) and wireless communication. Combined with one-way valve isolation and a closed wind tunnel circuit inside the cabin, it reduces the number of cross-cabin interfaces while taking into account the airtightness of the high-altitude environment simulation cabin and the accuracy of test measurements.

[0318] Pre-balancing-steady-state control-deceleration coupling chain:

[0319] In the in-cabin wind tunnel test system for high-altitude aerodynamic coupling testing of aircraft components described in this invention, the operation of the test system is not arbitrarily switched according to the start-stop method of ordinary equipment. Instead, it forms a complete operation coupling chain through three stages: pre-balancing, steady-state control, and slow-stop, so as to reduce the impact of human disturbance on the authenticity of the test and the stability of boundary conditions during the state switching process.

[0320] Specifically, in the pre-balancing phase, the high-altitude parameter adjustment system first establishes and adjusts the temperature, pressure and humidity inside the high-altitude environment simulation chamber, so that the environmental parameters inside the chamber reach the preset target value and remain stable for a predetermined period of time. During this period, the wind tunnel system inside the chamber remains in an unstarted state, thereby avoiding the interference of flow disturbances, heat and moisture migration and pressure fluctuations caused by wind tunnel operation on the background environment establishment process.

[0321] During the steady-state control phase, the wind tunnel system inside the cabin is started and operated. The two-way coupled environmental dynamic control system implements synchronous closed-loop adjustment of environmental parameters, wind speed in the test section, uniformity of the cabin environment, and dew point protection status, so that the background environmental field, local test flow field, and anti-condensation protection are coordinated and maintained stably under the same operating conditions.

[0322] During the slow-down phase, the wind tunnel fan is first decelerated to gradually release the test airflow load, and then the high-altitude parameter adjustment system is shut down after a delay to avoid sudden pressure changes, temperature and humidity drift and local condensation in the chamber caused by the shutdown transient.

[0323] Therefore, the above-mentioned pre-balancing-steady-state control-gradual shutdown process logic is a process control chain proposed for the dynamic behavior of high-altitude environment and cabin wind tunnel coupled test. It is used to ensure that the cabin wind tunnel test system for high-altitude environment aerodynamic coupling test of aircraft components described in this invention can maintain the authenticity, consistency and repeatability of the test boundary conditions during start-up, shutdown and operation condition switching.

[0324] Overall air path of the in-cabin wind tunnel test system for high-altitude environment aerodynamic coupling testing

[0325] This invention discloses an in-cabin wind tunnel test system for high-altitude aerodynamic coupling testing of aircraft components. The overall air path comprises two parts: an external air path and an internal air path. The external air path establishes the high-altitude environment, responsible for processing external gas to create the target high-altitude environment and delivering it into the environmental chamber. The external air path consists of an external clean gas input interface, a temperature control module, a pressure control module, a humidity control module, a one-way valve, and the environmental chamber, used to regulate the temperature, pressure, and humidity of the gas entering the environmental chamber to establish the target high-altitude simulated environment. The internal air path is an in-cabin wind tunnel circulation air path, a closed-loop wind tunnel circulation air path located inside the environmental chamber, responsible for creating the stable airflow required for the test within the environmental chamber. The internal air path consists of a wind tunnel fan, a contraction section, a pre-rectifier, a test section, a post-rectifier, a wind tunnel outlet, and an in-cabin recirculation zone, used to create a stable and uniform test airflow in the high-altitude simulated environment. The external air path determines the environmental parameters inside the cabin, while the internal air path determines the flow field parameters of the test section. The external and internal air paths work together to achieve coupled simulation of the high-altitude environment and aerodynamic loading.

[0326] From a system perspective, the gas flow of the in-cabin wind tunnel test system for high-altitude aerodynamic coupling testing of aircraft components described in this invention is not a single flow path, but is composed of two parts: an external air path and an internal air path. It forms a double-layer air path structure that couples environment establishment and test flow construction within the same high-altitude environment simulation cabin.

[0327] External gas path: Environmental gas path establishment

[0328] The external gas path is a gas regulation pathway located outside the environmental chamber, used to establish and maintain the simulated high-altitude background environment. External clean gas is first input into the system via the external clean gas input interface. Before entering the environmental chamber, it is preferably processed by the pressure control module, temperature control module, and humidity control module of the high-altitude parameter regulation system. The external gas path does not undertake the function of establishing the mainstream wind speed in the test section; its main function is to establish, regulate, and maintain the high-altitude background environmental parameters inside the environmental chamber. It is the environment establishment and maintenance gas path in the technical solution described in this invention.

[0329] Specifically, the main components of the external air path include an external clean gas input interface (28), a temperature control module (18), a pressure control module (19), a humidity control module (20), a one-way valve 1 (17), a one-way valve 2 (21), and a high-altitude environment simulation chamber (22).

[0330] Specifically, the inlet path of the external gas path can be represented as: "External clean gas input interface (28) → temperature control module (18) / pressure control module (19) / humidity control module (20) → one-way valve 1 (17) → high-altitude environment simulation chamber (22)";

[0331] Among them, the external clean gas input interface (28) is used to provide the system with clean and controllable initial gas; the temperature control module (18) is used to heat, cool or set the temperature of the input gas; the pressure control module (19) is used to adjust the pressure state of the input gas so that the environmental chamber reaches the chamber pressure level corresponding to the target simulated height; the humidity control module (20) is used to adjust the humidity parameters of the input gas so that the environmental chamber forms the target moisture content or target dew point conditions; the one-way valve 1 (17) is set on the inlet side of the external gas path to ensure that the adjusted gas enters the environmental chamber in a predetermined direction and to prevent the gas in the chamber from flowing back into the upstream adjustment module.

[0332] Furthermore, when the system needs to perform gas discharge, chamber pressure recovery or working fluid replacement, the external gas path preferably includes an outlet or recovery path, which can be expressed as: "High-altitude environment simulation chamber (22) → one-way valve 2 (21) → outlet end or recovery end";

[0333] Among them, the one-way valve 2 (21) is set on the outlet side of the external gas path to ensure that the gas in the cabin is discharged or recovered in a predetermined direction and to prevent external backflow from disturbing the target working conditions in the cabin.

[0334] The external gas path establishes and maintains the background air conditions inside the environmental chamber. Its main functions include: First, adjusting the external gas to the target high-altitude parameter state, that is, comprehensively processing the input gas through the temperature control module (18), pressure control module (19), and humidity control module (20) to achieve the temperature, pressure, and humidity conditions corresponding to the preset test conditions. Second, introducing the adjusted gas into the environmental chamber, so that a low-pressure, low-temperature, and variable-humidity high-altitude background environment is formed inside the high-altitude environment simulation chamber (22), providing basic environmental conditions for the wind tunnel test inside the chamber. Third, the external gas path can export or recover the gas inside the chamber when needed. For example, during chamber pressure adjustment, condition switching, environmental recovery, or safety protection, the gas inside the environmental chamber is discharged to the external outlet or introduced into the recovery end for processing and reuse. Fourth, the external air path suppresses backflow and improves system operation safety through one-way valves. One-way valve 1 (17) and one-way valve 2 (21) constrain the inlet and outlet flow directions respectively, avoiding reverse flow caused by pressure fluctuations, environmental disturbances or changes in the operating conditions of external equipment, thereby improving the accuracy of environmental regulation, system stability and operation safety.

[0335] It should be noted that the external air path is not the mainstream air path for wind tunnel testing. The mainstream airflow in the test section of this invention is established by the closed-loop wind tunnel system inside the chamber, that is, the wind tunnel fan (6) draws in the gas and drives it to circulate in the internal air path defined by the wind tunnel shell (24), thereby forming the target wind speed and target flow field quality in the test section (11).

[0336] The functions of the external gas path are as follows: to establish the overall background pressure of the environmental chamber and regulate the gas pressure so that the interior of the environmental chamber reaches the low-pressure state required for the corresponding simulated altitude; to establish the overall background temperature of the environmental chamber and regulate the gas temperature so that the chamber forms a preset low temperature or variable temperature environment; to establish the overall background humidity of the environmental chamber and regulate the gas humidity so that the chamber reaches the target humidity state or dew point condition; and to establish and maintain the target high-altitude background environment required for the experiment, and to replenish, exhaust, recover and maintain the environment inside the chamber.

[0337] Therefore, the external gas path is the environmental regulation gas path connecting the environmental chamber to an external gas source or parameter adjustment module. Its primary task is to provide the environmental chamber with a background gas environment that meets the requirements of high-altitude simulation, rather than directly undertaking the task of constructing the test flow rate. The core function of the external gas path is not to generate high-speed test airflow, but to provide a controlled high-altitude background environment within the chamber; the external gas path mainly addresses the "environmental parameter establishment problem." For this reason, the overall solution of this invention is achieved through the division of labor and cooperation between the external and internal gas paths: the external gas path is responsible for creating the environment; the internal gas path is responsible for creating the test flow; the two operate coupled within the same chamber and are coordinated and managed by a unified control system.

[0338] Internal air path: In-cabin wind tunnel recirculation air path

[0339] The internal air path is the test airflow path formed by the partial gas entering the environment chamber being drawn into the main flow channel defined by the wind tunnel shell under the action of the wind tunnel fan, and circulating along the closed-loop wind tunnel circuit. In the internal air path, after the gas obtains circulation power from the wind tunnel fan, it passes sequentially through the adjustable contraction section (7), the pre-rectifier 1 (8), the test section (9), and the post-rectifier 2 (12), and returns to the inlet of the wind tunnel fan (6) through the return flow path, thereby forming a closed-loop test flow inside the environment chamber. The internal air path is preferably defined by the wind tunnel shell as the main flow channel, and the wind tunnel fan provides circulation power, so that the air inside the chamber forms a controlled directional flow within the wind tunnel system. Therefore, the internal air path can also be understood as the tunnel-level air path or the main test air path in this invention.

[0340] The main components of the internal air passage include the wind tunnel fan (6), the contraction section (7), the pre-rectifier 1 (8); the test section (11), the post-rectifier 2 (12), the wind tunnel shell (24), and the internal recirculation space.

[0341] The internal air path can be represented as the following flow path: "Indoor air → wind tunnel fan (6) → contraction section (7) → front rectifier 1 (8) → test section (11) → rear rectifier (12) → wind tunnel outlet → indoor recirculation zone → back to the inlet of wind tunnel fan (6)".

[0342] In a preferred embodiment, the wind tunnel shell (24) constitutes the main boundary structure of the internal air passage, which is used to define the shape of the main channel of the closed-loop airflow; the wind tunnel fan (6) is arranged in the upstream area of ​​the main channel to draw in the air in the chamber and provide circulation power; the contraction section (7) is arranged downstream of the wind tunnel fan (6) to improve the local acceleration capability by changing the flow channel cross-sectional area; the pre-rectifier 1 (8) is arranged upstream of the test section (11) to improve the quality of the incoming flow entering the test section; the test section (11) is used to form the target wind speed and target flow field required by the test object; the post-rectifier (12) is arranged downstream of the test section (11) to correct the direction and redistribute the velocity of the exhaust flow; the airflow discharged through the wind tunnel outlet enters the return space in the chamber and then returns to the inlet of the wind tunnel fan (6), thereby forming a closed loop in the chamber.

[0343] The core task of the internal air path is to establish and maintain the main test airflow required for the test section. The specific functions of the internal air path are as follows: First, the internal air path can draw in air from the chamber and form a circulating flow. The wind tunnel fan (6) draws in air from inside the environmental chamber and makes the air circulate within the main flow channel defined by the wind tunnel shell (24). Second, the internal air path can form a controlled directional airflow inside the wind tunnel. Driven by the wind tunnel fan (6), accelerated by the contraction section (7), and guided by the wind tunnel shell (24), the air inside the chamber forms the main test airflow flowing in a predetermined direction. Third, the internal air path can generate a target wind speed in the test section. Through the combination of fan power compensation and the geometric acceleration capability of the contraction section, a target wind speed is established in the test section (11) to meet the requirements of aerodynamic testing of the test piece and high-altitude environmental coupling testing. Fourth, the internal air path can ensure the flow field quality through the front and rear rectifiers; the front rectifier 1 (8) is used to improve the uniformity of the incoming flow at the test section inlet and reduce the lateral velocity component; the rear rectifier (12) is used to regulate the downstream discharge flow of the test section, weaken the influence of the wake and non-uniform discharge state on the recirculation zone and inlet boundary, thereby improving the steady-state maintenance capability of the entire circulation loop. Fifth, the internal air path enters the recirculation zone inside the chamber through the outlet and achieves recirculation. After the airflow passes through the test section and the rear rectifier, it is discharged from the wind tunnel outlet and enters the recirculation space inside the chamber. Under the action of the recirculation organization inside the chamber, it returns to the inlet of the wind tunnel fan (6), thereby forming a closed-loop test flow.

[0344] The internal air path is the main test air path in this invention that truly undertakes the aerodynamic testing task. The internal air path can establish the target wind speed required for the test section; maintain the uniformity of the velocity, consistency of the flow direction, and the quality of the flow field of the incoming flow in the test section; and form a stable and repeatable closed-loop test flow in the cabin under low-pressure background conditions. The internal air path is not simply the natural flow of air in the cabin, but a closed-loop, directional, controllable, and stable test air path formed by the combined action of the wind tunnel fan (6), the contraction section (7), the rectifier, and the wind tunnel shell (24). The high-speed circulating airflow in the internal air path will affect the local wall temperature, local air state, and the risk of condensation or frost in the cabin through convective heat transfer and flow field disturbance. The core function of the internal air path is to construct and maintain the wind tunnel test airflow under a given high-altitude background environment; the internal air path mainly solves the "test flow establishment problem".

[0345] Relationship between external and internal air paths

[0346] This invention employs a dual-layer coupled gas path structure: the outer gas path is responsible for creating the environment; the inner gas path is responsible for creating the test flow. The low-pressure, low-temperature, and variable-humidity background environment established by the outer gas path directly determines the gas density, dew point temperature, and thermal-humidity state in the inner gas path, thus affecting the wind speed establishment capability, flow field stability, and condensation risk of the test section. Conversely, the circulating airflow in the inner gas path, through convective heat transfer, local pressure distribution, and flow field disturbances, affects the cabin wall temperature, local humid air state, and the risk of condensation or frosting. The outer and inner gas paths are not two separate systems, but rather form a unified gas path system within the same environmental chamber, with mutually coupled responses of "environmental parameter establishment - test flow construction - wall thermal-humidity."

[0347] Furthermore, the external air path is responsible for establishing the target high-altitude background environment, while the internal air path is responsible for establishing the target test flow within this background environment. Both operate coupled within the same environmental chamber and are coordinated and regulated through a unified control system. This invention can simultaneously establish a low-pressure, low-temperature, and variable-humidity environment corresponding to the simulated altitude within the chamber; construct stable test section wind speeds and flow field quality within the environment; and determine and suppress condensation or frosting risks in real time under airflow heat exchange and wall cooling conditions; enabling high-altitude environment simulation, wind tunnel steady-flow testing, and anti-condensation assurance to be completed collaboratively on the same platform.

[0348] The external gas path is responsible for creating the environment. Its main task is to regulate the state of the gas entering the environmental chamber through components such as the external clean gas input interface, temperature control module, pressure control module, humidity control module, and one-way valve, so as to establish and maintain the target high-altitude background environment inside the environmental chamber. The internal gas path is responsible for creating the test flow. Its main task is to drive a portion of the gas inside the environmental chamber into the mainstream channel defined by the wind tunnel shell through the wind tunnel fan, and then return to the recirculation zone after passing through the contraction section, rectifier, and test section, thereby establishing the target test airflow required by the test object.

[0349] Furthermore, the low-pressure, low-temperature, and variable-humidity background environment established by the external air path directly determines the gas density, dew point temperature, frost point temperature, and overall thermal and humid conditions in the internal air path. This, in turn, affects the ability to establish the target wind speed in the test section, the stability of the circulating flow field, and the risk of condensation or frost formation on the walls. In other words, if the external air path changes the chamber pressure, chamber temperature, or internal humidity, the characteristics of the test airflow in the internal air path, the difficulty of wind speed control, and the dew point safety margin will all change accordingly.

[0350] Conversely, the circulating airflow in the internal air path is not merely passively influenced by the background environment. During the test operation, it also affects the local wall temperature, local humid air conditions, and heat and humidity distribution inside the environmental chamber through convective heat transfer, changes in local pressure distribution, velocity field disturbances, and wake feedback, thereby further affecting the risk of condensation or frosting. For example, the high-speed incoming flow near the test section enhances local convective heat transfer to the walls, leading to a decrease in wall temperature; another example is that changes in the local flow distribution in the recirculation zone cause changes in the humidity of the microenvironment around the walls, thus altering the local dew point conditions.

[0351] The external and internal air paths are not two separate independent systems, but rather form a unified air path system within the same environmental chamber, where environmental parameters are established, test flow is constructed, and wall thermal and humidity responses are coupled. Within this unified air path system: the external air path determines the environmental background; the internal air path determines the test airflow; the wall thermal and humidity state is the result of the combined effects of both; and the control system coordinates these two processes based on wind speed, temperature, humidity, pressure, and wall temperature. The essence of this invention is not simply the superposition of "environmental chamber functions" and "wind tunnel functions," but rather the synergistic coupling of external environment establishment and internal test flow construction within a unified, controlled space. The external air path is responsible for establishing the target high-altitude background environment, while the internal air path is responsible for establishing the target test flow within that background environment. Both operate coupled within the same environmental chamber and are coordinated and regulated through a unified control system.

[0352] Explanation of the overall airflow configuration and the coupling relationship between the external and internal airflow paths

[0353] This invention provides an integrated high-altitude environment wind tunnel test platform with dual-layer coupling of external and internal air paths, and coordinated operation of environment setup, test flow construction, and dew point anti-condensation. This overall system configuration significantly improves the realism of test conditions, steady-state maintenance capability, repeatability, and system operational reliability.

[0354] Thus, the entire system described in this invention forms a synergistic effect at four levels:

[0355] (1) Environment establishment layer: The external air path and the high-altitude parameter adjustment system are responsible for establishing the target cabin pressure, target temperature and target humidity inside the environmental cabin, so that the environmental cabin forms a low-pressure, low-temperature and variable humidity background environment corresponding to the preset high-altitude conditions.

[0356] (2) Test flow construction layer: The internal air path and closed circulation wind tunnel system are responsible for establishing the target wind speed of the test section under the above background environment, and the uniformity of the incoming flow, the consistency of the flow direction and the quality of the flow field are ensured by the wind tunnel fan, the contraction section and the front and rear rectification structures.

[0357] (3) Thermal and humidity safety protection layer: The wall surface temperature detection unit, dew point or frost point calculation unit and local heating unit jointly complete the monitoring of wall surface thermal and humidity status and anti-condensation control. Under the conditions of airflow heat exchange, wall surface cooling and environmental changes, it can determine in real time whether there is a risk of condensation or frost, and implement local heating or operating condition coordination constraints when necessary.

[0358] (4) Unified supervision and coordination layer: The unified control system comprehensively coordinates the external and internal air paths, not only adjusting the target parameters of the environmental chamber and the target wind speed of the test section, but also limiting, arbitrating and switching the steady flow execution amount, environmental switching rate and heat replenishment intensity according to the condensation safety margin, so as to ensure that the high-altitude environment simulation, wind tunnel steady flow test and dew point anti-condensation guarantee can be completed in the same platform.

[0359] Because of the system architecture, this invention can simultaneously achieve the following objectives: establish a low-pressure, low-temperature, and variable-humidity background environment corresponding to the simulated altitude inside the environmental chamber; construct a stable target wind speed for the test section in this background environment and maintain the required flow field quality; determine and suppress the risk of condensation or frost in real time under airflow heat exchange and wall cooling conditions; and make high-altitude environment simulation, wind tunnel steady flow test, and anti-condensation protection no longer isolated actions, but collaboratively completed under the same control framework.

[0360] Description of Controlled Objects, Manipulated Variables, and Control Strategies

[0361] In the low-pressure high-altitude environment cabin wind tunnel stabilization construction and dew point anti-condensation linkage control system described in this invention, the controller's controlled object is not a single parameter, but a multi-variable coupled object including at least the test section wind speed, cabin pressure, cabin temperature, cabin humidity, and cabin environmental uniformity. Specifically, the controlled variables include at least: the representative wind speed V of the test section (11), the environmental cabin gas pressure P, gas temperature T, and gas humidity RH, and the temperature difference index ΔT and humidity difference index ΔRH characterizing the uniformity of the cabin space. Among them, the representative wind speed of the test section is used to characterize the wind tunnel main test flow construction state; pressure, temperature, and humidity are used to characterize the high-altitude environmental background conditions; the temperature difference index and humidity difference index are used to characterize whether the cabin space environment distribution is uniform, thereby reflecting the degree of environmental homogenization and the level of local thermal and humidity deviation.

[0362] Corresponding to the aforementioned controlled quantities, the operable quantities of the present invention include at least the wind tunnel fan (6) rotational speed n, the effective area At of the throat of the adjustable contraction section (7), the execution quantity of the environmental control module, and the control quantity of the environmental homogenizing fan array. Among them, the wind tunnel fan (6) rotational speed n determines the total pressure rise capacity and circulation flow capacity of the closed circulation air path, and is the dynamic side execution quantity of the flow stabilization construction; the effective area At of the throat of the adjustable contraction section (7) is equivalent to a variable throttling component, which adjusts the system flow-pressure ratio operating point by changing the effective flow area of ​​the flow channel, and is the geometric side execution quantity of the flow stabilization construction; the environmental control module is used to regulate the background environment of pressure, temperature and humidity; the environmental homogenizing fan array (3 and 16) is used to reduce the temperature gradient and humidity gradient inside the chamber and improve spatial uniformity.

[0363] In this invention, there are several key disturbances and uncertainties during system operation. Among them, one of the most significant disturbances is the change in gas density ρ(P,T) with variations in chamber pressure and temperature. Since air density is highly sensitive to pressure and temperature changes under low-pressure high-altitude simulation conditions, even if the wind tunnel fan speed n and the effective throat area At remain constant, the actual wind speed in the test section (11) will still deviate with density changes. In addition, system start-up and shutdown, operating condition switching, and sudden changes in control quantities also cause pressure fluctuations in the chamber, changes in the spatial gradient of temperature and humidity, and an increased risk of local condensation, thereby having a coupled impact on the flow field stability and the ability to maintain the high-altitude environment in the test section.

[0364] Based on the above-mentioned control object, manipulated quantity, and disturbance characteristics, the present invention preferably adopts a composite control strategy consisting of trajectory planning, model feedforward compensation, feedback closed-loop regulation, execution quantity limiting protection, and operating state switching. In other words, the core of the control of the present invention does not rely solely on a single control method, but rather combines "slope trajectory planning + feedforward compensation + PID feedback correction + limiting protection + state switching" into a unified control framework to achieve coordinated operation between low-pressure high-altitude environment simulation, test section (11) steady flow construction, and anti-condensation protection.

[0365] Specifically, when the target wind speed, target cabin pressure, target temperature, or target humidity need to be switched, the controller (23) preferably performs trajectory planning on the target value first, rather than directly using a step input. Preferably, the change in the target value can be converted from a step form to a ramp form or a smooth transition curve form to reduce the risk of pressure shock, wind speed overshoot, enhanced local heat transfer, and sudden drop in wall temperature caused by sudden changes in the execution quantity. Thus, ramp trajectory planning is mainly used to reduce the transient coupling disturbance of the system during the transition of operating conditions.

[0366] In terms of feedforward compensation, the controller preferably calculates the current gas density ρ(P,T) based on the real-time collected pressure P and temperature T, and performs feedforward correction on the target values ​​of the wind tunnel fan speed n and the effective area At of the throat of the adjustable contraction section based on the density change. In this way, the impact of density changes on the wind speed establishment capability under low-pressure variable pressure conditions can be pre-compensated before the wind speed deviation has accumulated significantly, thereby improving the steady flow establishment speed and reducing the hysteresis error caused by pure feedback control.

[0367] In terms of feedback control, the controller preferably adopts PID control or its equivalent closed-loop control form to perform closed-loop correction on the wind speed, environmental parameters and uniformity index of the test section (11). For wind speed control, the controller adjusts the wind tunnel fan speed n or the effective throat area At according to the deviation between the representative wind speed and the target wind speed of the test section (11); for environmental parameter control, the controller adjusts the corresponding environmental adjustment module according to the deviation of pressure, temperature and humidity; for environmental uniformity control, the controller adjusts the working state of the homogenizing fan array according to the temperature difference ΔT and humidity difference ΔRH in the chamber to reduce the spatial gradient. Thus, feedback control is mainly used to correct model uncertainty, external disturbances and feedforward compensation errors.

[0368] To ensure system operational safety and hardware feasibility, this invention also sets amplitude limits and rate-of-change constraints for each actuator. Preferably, upper limits, lower limits, or rate-of-change limits are set for the wind tunnel fan speed n, the effective throat area At, the output of the environmental control module, and the control quantities of the homogenizing fan array, respectively, to avoid actuator saturation, mechanical shock, control oscillation, excessive local heat transfer, or wall temperature overshoot. Furthermore, when the condensation safety margin is insufficient, the controller can further impose additional restrictions on fan speed increase, throat change rate, or target wind speed trajectory, ensuring that the steady-flow control operates within the feasible domain that meets the anti-condensation constraints.

[0369] Furthermore, this invention preferably employs a state switching mechanism to manage the entire system in stages. The state switching can be implemented using a state machine, mode logic, or an equivalent switching strategy. For example, the system can switch between a pre-balancing mode, an environment establishment mode, a low-pressure stable flow construction mode, a condensation risk intervention mode, a steady-state test mode, and a degradation protection mode. In different modes, the controller can assign different priorities to wind speed control, environmental control, anti-condensation control, and homogenization control, and adjust the feedforward weight, feedback gain, execution boundary, and protection threshold. This ensures that the system maintains clear control objectives, clear execution logic, and balances test reliability and safety in different operating stages.

[0370] Overall, this invention employs a composite control system for wind tunnel testing in low-pressure, high-altitude environments. It is a multi-objective coupled control framework built around multiple controlled variables, actuators, and disturbance sources. By reducing abrupt changes in operating conditions through ramp trajectory planning, mitigating the impact of density variations through feedforward compensation, achieving error correction through PID feedback, ensuring execution safety through amplitude limiting protection, and coordinating control objectives at different stages through state switching, this invention can simultaneously establish a high-altitude background environment, maintain the target wind speed in the test section, homogenize the cabin environment, and suppress the risk of condensation or frost within the same system. This improves the realism, stability, and repeatability of high-altitude environment coupled testing.

[0371] An in-cabin wind tunnel testing method for high-altitude aerodynamic coupling testing of aircraft components

[0372] The present invention describes an in-cabin wind tunnel test method for aerodynamic coupling testing of aircraft components in a high-altitude environment. Under low-pressure high-altitude simulated conditions, the wind speed, cabin pressure, temperature, humidity, spatial uniformity, and risk of wall condensation in the test section are controlled in a coordinated manner.

[0373] The basic idea of ​​the in-cabin wind tunnel test method for high-altitude aerodynamic coupling testing of aircraft components, as described in this invention, is as follows: First, the target test conditions are set, including target wind speed, target air pressure, target temperature, and target relative humidity; then, the target environment inside the cabin is established and maintained through a high-altitude parameter adjustment system; after the environment reaches pre-equilibrium, the wind tunnel system is started, and the target wind speed of the test section is established through the coordinated action of the wind tunnel fan and the adjustable contraction section; during the test operation, the control system continuously collects the temperature, humidity, and pressure status inside the cabin, the gas status of the wind tunnel, the wind speed of the test section, and the temperature of the wind tunnel shell wall, and performs flow stabilization control, environmental uniformity control, and anti-condensation control based on these real-time data; when the cabin pressure changes and the gas density decreases, the wind speed is compensated by synchronously increasing the fan speed and reducing the effective cross-sectional area of ​​the throat of the contraction section.

[0374] When the temperature or humidity difference inside the cabin exceeds the threshold, the environmental homogenization fan array is activated to reduce the spatial gradient.

[0375] When the wall temperature is close to or lower than the dew point temperature of the air inside the cabin, the anti-condensation electric heating film is automatically activated to provide localized supplemental heating.

[0376] At the end of the test, the system should be gradually shut down in the order of first stopping the wind tunnel and then retreating to the environment to avoid pressure fluctuations, wall condensation or equipment impact.

[0377] The in-cabin wind tunnel test method for aerodynamic coupling testing of aircraft components in high-altitude environment described in this invention is essentially a collaborative control method of "stabilizing flow construction - environmental homogenization - dew point anti-condensation" for wind tunnel testing in low-pressure high-altitude environment.

[0378] Furthermore, the in-cabin wind tunnel testing method for high-altitude aerodynamic coupling testing of aircraft components described in this invention comprises the following steps:

[0379] S1. Set target operating conditions: The operator inputs the target test operating condition parameters through the human-machine interface, including target wind speed, target air pressure, target temperature and target relative humidity;

[0380] For example, the target wind speed can be set to 50 m / s, the target air pressure can be set to 26 kPa, the target temperature can be set to -50℃, and the target relative humidity can be set to 30%RH;

[0381] The target parameters serve as a unified benchmark for subsequent environmental conditioning, flow stabilization, and anti-condensation control.

[0382] S2. Environmental pre-equilibrium: Activate the high-altitude parameter adjustment system, and input the regulated gas into the environmental chamber through the temperature control module, pressure control module and humidity control module, and control the unidirectional flow of gas through the one-way valve;

[0383] Specifically, the high-altitude parameter adjustment system is activated, injecting regulated gas into the chamber, while check valves 1 (17) and 2 (21) are opened; after the chamber's air pressure, temperature, and humidity reach the target values ​​and stabilize for 15 minutes, the next step is initiated. During this stage, the wind tunnel fan (6) remains closed to prevent airflow disturbances from affecting the environmental setup;

[0384] During the environmental pre-equilibrium phase, the wind tunnel fans are kept off, and the adjustable contraction section is preferably kept at a large opening to avoid the main airflow of the wind tunnel disturbing the establishment of the cabin environment.

[0385] Meanwhile, the temperature and humidity distribution inside the cabin is monitored in real time by an array of temperature and humidity sensors, and an environmental equalization fan array is driven to operate when necessary to reduce temperature and humidity differences inside the cabin.

[0386] Once the cabin air pressure, temperature, and humidity all reach the target values ​​and remain stable for a preset time, such as 10 to 30 minutes, preferably about 15 minutes, the system enters the next stage.

[0387] S3. Start the wind tunnel and execute bidirectional coupling control: the wind tunnel fan (6) starts, and the wind speed sensor in the test section provides real-time feedback of the actual wind speed.

[0388] If the measured wind speed is lower than the set value, the computer (23) synchronously increases the fan speed and instructs the contraction section (7) to reduce the throat cross-sectional area to compensate for the effect of the decrease in gas density under low pressure; at the same time, the temperature and humidity sensor array (2) continuously monitors the uniformity of the environment inside the chamber, and once unevenness is detected, the intelligent environmental homogenization fan array (3, 16) is activated; in addition, the wind tunnel wall temperature sensor (5) and the temperature and humidity data inside the chamber are used to calculate the dew point temperature in real time. When the wall temperature of the wind tunnel shell (24) is lower than the dew point, the system automatically activates the electric heating film (4) for heating protection to prevent condensation;

[0389] After the environmental pre-equilibrium is completed, the wind tunnel fan (6) is started to establish the target wind speed of the test section. The wind tunnel wall temperature sensor (5) in the test section (11) provides real-time feedback on the actual wind speed. The controller adjusts the speed of the wind tunnel fan (6) and the effective cross-sectional area of ​​the throat of the adjustable contraction section (7) in a coordinated manner according to the deviation between the actual wind speed and the target wind speed.

[0390] When the measured wind speed is lower than the target value, the controller increases the speed of the wind tunnel fan (6) or decreases the effective cross-sectional area of ​​the throat of the adjustable contraction section (7) to enhance the circulation power and local acceleration capability; when the measured wind speed is higher than the target value, the controller correspondingly decreases the speed of the wind tunnel fan (6) or increases the effective cross-sectional area of ​​the throat of the adjustable contraction section (7).

[0391] Meanwhile, the controller (23) calculates the gas density based on the cabin pressure and gas temperature, and uses the density as a feedforward compensation amount to correct the wind tunnel fan (6) speed command and the adjustable contraction section (7) opening command, so as to compensate for the influence of density change on wind speed under low pressure transformation conditions.

[0392] In addition, the temperature and humidity sensor array continuously monitors the uniformity of the cabin environment. When the temperature difference between any two points exceeds ±1℃ or the humidity difference exceeds ±5%RH, the intelligent environmental homogenization fan array 1 (3) and the intelligent environmental homogenization fan array 2 (16) are activated to reduce the spatial gradient and improve the environmental uniformity.

[0393] At the same time, the controller (23) calculates the dew point temperature in real time based on the temperature, humidity and pressure of the gas inside the chamber, and compares it with the local wall temperature measured by the wind tunnel wall temperature sensor (5). When the wall temperature is lower than the dew point temperature or lower than the dew point temperature plus a preset safety margin, the anti-condensation electric heating film (4) is automatically activated to provide local heating to the easily condensable areas of the wind tunnel shell (24) or the outer wall of the test section (11) to suppress condensation or frost.

[0394] S4. Data acquisition and model testing: Under stable working conditions, the wireless measurement and control support rod completes the model angle of attack adjustment and transmits the six-dimensional force data back to the computer (23) through the UWB wireless protocol to achieve high-precision measurement without cabin penetration.

[0395] After the various working parameters stabilize, the model testing phase begins. The fully built-in wireless measurement and control support rod (25) and attitude adjustment mechanism (27) in the test section (11) adjust the attitude of the test piece (10). The six-dimensional force measurement unit (26) acquires the force data of the test piece and transmits the measurement data back to the industrial computer through the UWB wireless communication interface (29).

[0396] During the data acquisition and model testing phase, the controller (23) continuously maintains the target wind speed, target environmental parameters, spatial uniformity, and anti-condensation state of the wall, thereby ensuring that the model test is carried out under stable, realistic, and repeatable working conditions.

[0397] S5. Slow Stop and Reset: After the test, the system first gradually reduces the fan speed to zero, then shuts down the high-altitude parameter adjustment system after a 2-minute delay, and finally shuts down all auxiliary equipment to prevent pressure fluctuations or condensation in the cabin due to sudden shutdown.

[0398] After the test, the system does not directly shut down all actuators, but instead implements a slow stop in a safe sequence. First, the speed of the wind tunnel fan (6) is gradually reduced to zero, and the effective cross-sectional area of ​​the throat of the adjustable contraction section (7) is gradually restored to a larger opening to reduce sudden airflow changes. Then, a preset time is delayed, for example, about 2 minutes, to allow the residual flow in the chamber to gradually decay and the heat exchange to tend to balance. Subsequently, the temperature control module (18), pressure control module (19), and humidity control module (20) are gradually shut down to avoid pressure fluctuations or sudden environmental changes in the chamber due to rapid shutdown. During the entire slow stop process, the controller (23) continuously monitors the relationship between the wall temperature and the dew point temperature. If the local wall temperature is still lower than the dew point temperature plus a safety margin, the anti-condensation electric heating film (4) is maintained or activated until the wind tunnel fan (6) stops completely and the environmental control system is shut down. Finally, the system shuts down the auxiliary equipment and enters standby or reset state.

[0399] Through the above-described embodiments, this invention achieves deep coupling between wind tunnel aerodynamic loads and the high-altitude multidimensional environment, solving key problems in traditional solutions such as environmental distortion, unstable flow field, easy condensation, and poor sealing. It provides a high-fidelity, high-reliability, and fully automated ground verification platform for aircraft components. This invention can first establish a stable low-pressure, low-temperature, and variable-humidity high-altitude background environment within the environmental chamber, then construct the target test wind speed within this background environment, and simultaneously execute environmental uniformity control and dew point anti-condensation control throughout the entire test process. This achieves synergistic linkage between high-altitude environment simulation, wind tunnel steady-flow testing, and anti-condensation protection, improving the realism, stability, and repeatability of the test conditions.

[0400] Therefore, the in-cabin wind tunnel test system for high-altitude aerodynamic coupling testing of aircraft components described in this invention is an integrated coupling system that forms mechanical, fluid, and electrical connections around the goal of synchronously constructing high-altitude low-pressure, low-temperature, controlled humidity, and airflow fields. The environmental parameter establishment and homogenization subsystems, as well as wireless measurement and sealing subsystems, work together to achieve high-fidelity testing of aircraft components in a real high-altitude coupling environment. The technical solution described in this invention is not a simple assembly of existing wind tunnels and environmental chambers, but rather a systematic and coordinated overall improvement addressing the contradictions in flow field quality, environmental uniformity, condensation control, and sealing measurement in multi-physics coupling tests.

[0401] Example 1: Specific Implementation of the In-cabin Wind Tunnel Test System for High-Altitude Environment Aerodynamic Coupling Testing of Aircraft Components according to the present invention, wherein the wind tunnel is integrally embedded inside the high-altitude environment simulation cabin and forms a closed-loop air path.

[0402] The present invention discloses an in-cabin wind tunnel test system for high-altitude aerodynamic coupling testing of aircraft components. In embodiment 1, the in-cabin wind tunnel test system for high-altitude performance testing of aircraft components adopts an in-cabin integrated closed-loop wind tunnel configuration. This involves embedding a closed micro-wind tunnel entirely inside a sealed high-altitude environment simulation chamber to form an in-cabin closed-loop airflow path, reducing cross-cabin interfaces and external disturbances. Specifically, the wind tunnel test system is not set up as an independent external device outside the high-altitude environment simulation chamber and then combined with the environment chamber through cross-cabin pipes, interfaces, or external connection channels. Instead, it is arranged as a whole inside the high-altitude environment simulation chamber body (22) and forms a relatively independent closed-loop gas loop inside the chamber. The in-cabin integrated closed-loop wind tunnel configuration allows the wind tunnel system's airflow generation, rectification, acceleration, test loading, and recirculation processes to all be completed inside the high-altitude environment simulation chamber, thereby avoiding the risks of pressure drop, heat loss, humidity drift, and leakage caused by cross-cabin transport, interface connections, and external airflow in the traditional "wind tunnel + environment chamber" separate combination scheme.

[0403] Specifically, the wind tunnel test system includes at least a wind tunnel fan (6), a contraction section (7), a rectifier 1 (8), a test section (11), and a return flow channel connected thereto. The components are arranged end-to-end according to the airflow circulation direction to form a closed flow path. The wind tunnel fan (6) is used to provide driving force for the circulating airflow; the contraction section (7) is used to further accelerate the incoming flow from the return section and establish the required test flow velocity; the rectifier 1 (8) is located between the contraction section (7) and the test section (11), and its interior is equipped with a honeycomb guide array and a multi-layer metal wire mesh rectifier layer to weaken large-scale vortices, suppress turbulence, and improve the uniformity of flow velocity distribution; the test section (11) is used to install the components of the aircraft under test and form a stable working flow field that meets the test requirements; the downstream airflow of the test section returns to the inlet of the wind tunnel fan (6) through the return flow channel, thereby completing the closed circulation inside the cabin. Preferably, the return flow channel is integrally formed with the main shell of the wind tunnel and is fixed as a whole to the internal support frame of the environmental cabin to improve the structural compactness and system integration.

[0404] In one specific implementation, the high-altitude environment simulation chamber is mainly used to establish the low-pressure, low-temperature, and target humidity environment outside the wind tunnel. The high-altitude parameter adjustment system regulates the overall environmental state inside the chamber through the temperature control module (18), pressure control module (19), and humidity control module (20). Since the wind tunnel is placed inside the high-altitude environment simulation chamber, the external boundary environment of the wind tunnel circulation loop is consistent with the high-altitude environment inside the chamber. Therefore, the circulating medium in the wind tunnel test section (11) can be continuously constrained by the high-altitude environmental field inside the chamber during the flow process, so that the target wind speed conditions, target air pressure, target temperature, and target humidity conditions are uniformly established within the same system platform. Compared with the traditional technical route of introducing airflow from the external wind tunnel to the environmental chamber, the integrated closed circulation structure inside the chamber can significantly reduce the number of cross-chamber interfaces, reduce the difficulty of system airtight control, and reduce the flow quality degradation caused by long-distance transportation.

[0405] Furthermore, to prevent condensation on the surface of the wind tunnel shell under low temperature and high humidity conditions, an electric heating film (4) is installed on the outer wall of the wind tunnel shell and electrically connected to the wall temperature sensor and the cabin temperature and humidity sensor array (2). The bidirectional coupled environmental dynamic control system controls the electric heating film (4) to start and stop as needed based on the comparison results of the wall temperature and the dew point temperature, so as to prevent condensation from interfering with the wind tunnel structure, sensing measurement and the surface condition of the specimen. At the same time, the intelligent environmental homogenizing fan array 1 (3) and the intelligent environmental homogenizing fan array 2 (16) can automatically operate according to the temperature and humidity distribution status of multiple points in the cabin, so as to reduce the non-uniformity of the external environmental field of the wind tunnel and ensure that the closed circulation wind tunnel works in a stable and uniform high-altitude simulated background environment.

[0406] Before the experiment begins, the high-altitude parameter control system pre-adjusts the air pressure, temperature, and humidity inside the environmental chamber. Once the environmental parameters inside the chamber reach the set values ​​and remain stable, the wind tunnel fan (6) is started to establish a closed-loop airflow. The wind tunnel wind speed sensor detects the actual wind speed in the test section (11) in real time and feeds the detection results back to the computer (23). The computer (23) adjusts the speed of the wind tunnel fan (6) and the effective throat cross-sectional area of ​​the contraction section (7) in conjunction with the deviation between the set wind speed and the measured wind speed to compensate for the influence of gas density changes on the flow velocity establishment capability under low pressure. After the experiment, the speed of the wind tunnel fan (6) is gradually reduced to allow the closed-loop airflow to decay smoothly, and then the environmental control unit is turned off to avoid sudden changes in the flow field, pressure fluctuations, or local condensation caused by sudden stop.

[0407] By adopting the aforementioned integrated closed-loop wind tunnel structure, Embodiment 1 achieves integrated operation of the wind tunnel system and the high-altitude environment simulation chamber, unlike the existing configuration where the wind tunnel and environment chamber are arranged side-by-side and connected separately. This implementation not only facilitates the simultaneous establishment of wind fields and high-altitude environmental fields within the same enclosed space, but also reduces interface leakage, minimizes boundary condition disturbances, and improves the stability and repeatability of test conditions. This provides a unified, stable, and high-fidelity test foundation for evaluating the aerodynamic performance, thermodynamic characteristics, and environmental adaptability of aircraft components under complex high-altitude conditions.

[0408] Example 2: Specific Implementation of the Dual-Domain Coordination of High-Altitude Temperature, Pressure, and Humidity Environment and Test Flow Field in an In-Cavity Wind Tunnel Test System for High-Altitude Aerodynamic Coupling Testing of Aircraft Components as Described in this Invention

[0409] In Example 2, the in-cabin wind tunnel test system for high-altitude performance testing of aircraft components adopts a dual-domain coordinated control approach for high-altitude temperature, pressure, and humidity environment and test flow field. Specifically, this example does not only control the target wind speed within the wind tunnel test section (11) separately, nor does it only statically adjust the air pressure, temperature, and humidity within the high-altitude environment simulation chamber. Instead, it treats the flow field quality control of the test section and the uniformity control of the in-cabin environment as two interconnected controlled domains, which are uniformly coordinated and scheduled by a two-way coupled environmental dynamic control system. This allows the test specimen to complete the test under stable, uniform, and engineering-representative high-altitude comprehensive working conditions.

[0410] Specifically, the first controlled domain is the flow field domain of the wind tunnel test section. Its core control objective is to ensure that the airflow velocity, flow direction stability, flow field uniformity, and turbulence intensity within the test section (11) meet the test requirements. To this end, the wind tunnel fan (6) adopts a variable frequency speed control method, the contraction section (7) adopts an adjustable throat cross-sectional area structure, and the rectifier 1 (8) adopts a honeycomb guide array and a multi-layer metal wire mesh composite rectification configuration. During the test, the wind speed sensor installed in the test section (11) collects the airflow velocity parameters in real time and feeds the detection signal back to the computer (23). After comparing the measured wind speed with the target wind speed, the computer (23) implements linkage adjustment of the rotation speed of the wind tunnel fan (6) and the effective contraction ratio of the contraction section (7) to maintain the stability of the target wind speed and flow field quality within the test section. Preferably, when the pressure inside the chamber decreases, resulting in a decrease in the density of the circulating medium, the system simultaneously increases the speed of the wind tunnel fan (6) and appropriately reduces the cross-sectional area of ​​the throat of the contraction section (7) to compensate for insufficient momentum under low-density conditions, thereby avoiding wind speed attenuation, velocity distribution distortion, or flow field quality degradation in the test section.

[0411] The second controlled domain is the high-altitude environment simulation chamber environment domain. Its core control objective is to ensure that the air pressure, temperature and relative humidity in the environment chamber reach the predetermined target values ​​and are sufficiently uniform in spatial distribution, so as to reduce the additional impact of environmental gradient on the test results of the specimen. To this end, the temperature control module (18), pressure control module (19) and humidity control module (20) pre-process the gas entering the environment chamber and collect the distribution of environmental parameters in each area in real time through the temperature and humidity sensor array (2) and air pressure sensor arranged at multiple points in the chamber. The computer (23) judges the uniformity of the environment in the chamber based on the real-time acquisition results; when the temperature difference between any two points exceeds the preset threshold, such as ±1℃, or the relative humidity difference exceeds the preset threshold, such as ±5%RH, the intelligent environment homogenizing fan array 1 (3) or intelligent environment homogenizing fan array 2 (16) is automatically started, and its speed and running time are adjusted to enhance the mixing of gas and heat and humidity exchange in the chamber, reduce the temperature and humidity deviation in the local area, until the environmental uniformity is restored to the set range.

[0412] The key to Example 2 is that the two controlled domains do not operate independently, but are controlled collaboratively through a bidirectional coupled environmental dynamic control system. Specifically, the establishment and maintenance of the flow field in the test section will disturb the overall temperature and humidity distribution in the environmental chamber. For example, the operation of the wind tunnel circulating airflow will cause local heat exchange enhancement, accelerated humidity migration and changes in the environmental gradient in the chamber. Conversely, changes in air pressure, temperature and humidity in the chamber will also directly affect the density, viscosity, sound speed and flow resistance characteristics of the wind tunnel circulating medium, thereby affecting the wind speed establishment capability, rectification effect and turbulence development state in the test section. Therefore, the computer (23) reads the real-time data of the wind speed sensor, air pressure sensor, temperature and humidity sensor array (2) and wall temperature sensor during the control process, comprehensively judges the coupling state between the wind field domain and the environmental domain, and implements joint adjustment of the wind tunnel fan (6), contraction section (7), temperature control module (18), pressure control module (19), humidity control module (20) and intelligent environmental homogenization fan array (3, 16) according to the set control logic.

[0413] Specifically, under low pressure and low temperature conditions, when the system detects that the actual wind speed of the test section has decreased due to the depressurization of the environmental chamber, the computer (23) increases the speed of the wind tunnel fan (6) and adjusts the cross-sectional area of ​​the throat of the contraction section (7) to maintain the target wind speed. On the other hand, in order to avoid the wind tunnel operation from intensifying local heat exchange in the chamber and causing environmental stratification to worsen, the intelligent environmental homogenization fan array (3, 16) is controlled to operate simultaneously to suppress temperature and humidity distribution deviations. For example, under high humidity and low temperature conditions, when the local humidity in the environmental chamber rises and approaches the condensation boundary, in addition to continuing to maintain the target wind speed of the test section, the system also adjusts the output of the humidity control module (20) and the operating status of the homogenization fan array according to the temperature and humidity distribution at multiple points in the...

Claims

1. A cabin wind tunnel test platform-level system for high-altitude performance testing of aircraft components, integrating a high-altitude multi-parameter coupled test chamber, characterized in that, The in-cabin wind tunnel test platform system consists of an environmental cabin body layer, an in-cabin wind tunnel layer, a parameter adjustment layer, and a closed-loop control layer. It integrates the entire in-cabin closed wind tunnel test system inside the high-altitude environment simulation cabin and forms an integrated installation with the high-altitude environment simulation cabin. The environmental cabin body layer, as the high-altitude environment matrix for dynamic homogenization, includes an environmental cabin body (22) and an environmental cabin body insulation layer (1) set on the outside of the environmental cabin body (22). It can construct and maintain a high-altitude background environment with low air pressure, low temperature and set humidity in a closed space. The intelligent environmental homogenization fan array 1 (3) and the intelligent environmental homogenization fan array 2 (16) are respectively installed in the upper and lower areas of the inner wall of the high-altitude environment simulation cabin, forming an upper and lower partitioned homogenization arrangement facing the overall background environment field inside the cabin. The environmental cabin body insulation layer (1) can suppress the heat exchange between the cabin and the outside under low temperature conditions, improve the stability maintenance capability of the low temperature background environment and reduce the environmental drift caused by the operation of the wind tunnel. It can also suppress the macroscopic temperature and humidity gradient caused by the operation of the built-in wind tunnel in the cabin through multi-point sensing and active homogenization mechanism, so that the test airflow circulates independently inside the closed high-altitude environment cabin and does not directly exchange with the outside, providing stable and consistent environmental boundary conditions for the test section (11). The wind tunnel layer inside the cabin is a closed-loop, controllable wind tunnel test channel established inside the sealed high-altitude environment cabin, which can ensure the quality of the flow field. The wind tunnel fan (6), adjustable contraction section (7), rectifier (8) and test section (11) are connected in series along the airflow direction and together with the wind tunnel shell (24) form a closed-loop wind tunnel circuit set in the high-altitude environment simulation cabin, so that the test airflow forms an independent circulation in the cabin and does not directly exchange with the outside. The anti-condensation electric heating film (4) is attached to the outer wall of the wind tunnel shell (24) to provide local heating protection for the wind tunnel shell (24) and the adjacent area of ​​the test section (11). It can carry the measurement and control components in the test section (11) and realize wireless data transmission and power supply management. The test component (10) is installed inside the test section (11) through the fully built-in wireless measurement and control support rod (25). The operation of the wind tunnel fan (6), adjustable shrink section (7) compensation, composite rectification and anti-condensation protection maintains a stable, uniform and measurable test flow field under low pressure, low temperature and variable humidity conditions, providing the test piece (10) with local aerodynamic loading conditions in a real high-altitude environment; the test piece (10) is installed inside the test section (11) through a fully built-in wireless measurement and control support rod (25); the fully built-in wireless measurement and control support rod (25) is completely arranged inside the high-altitude environment simulation chamber and extends into the test section (11) to realize the installation support and attitude adjustment of the test piece (10) without wiring through the chamber and without setting external support components through the chamber; in addition, multiple sensors are set in the wind tunnel layer inside the chamber, which work together with the wind tunnel fan (6), adjustable shrink section (7), rectifier (8) and test section (11) to ensure the operation of the wind tunnel test chamber; The parameter adjustment layer, consisting of a temperature control module (18), a pressure control module (19), a humidity control module (20), an external clean gas input interface (28), and one-way valves (17 and 21) located between the parameter adjustment layer and the high-altitude environment simulation chamber, constitutes a background parameter supply and dynamic maintenance subsystem for high-altitude environment-wind tunnel coupled test conditions. The temperature and humidity sensor array (2) is fixedly installed in multiple spatial locations inside the high-altitude environment simulation chamber, at least at multiple installation points in the upper, lower, and adjacent areas of the test section (11) of the chamber, which can characterize the spatial stratification and gradient of temperature and humidity inside the chamber and obtain spatial distribution information of temperature and humidity parameters inside the chamber. The high-altitude parameter preprocessing unit includes an external gas input interface and a temperature control module (18) arranged in series along the external gas flow direction. The pressure control module (19) and humidity control module (20) pre-process external gas in the order of temperature-pressure-humidity before inputting it into the sealed high-altitude environment chamber. One-way valves (17) and (21) are set on the gas exchange path between the parameter adjustment layer and the high-altitude environment simulation chamber. They can restrict the backflow and return of gas in the chamber to the parameter adjustment layer along the parameter adjustment path. Under the disturbance conditions of the closed-loop wind tunnel operation in the chamber, the parameter supply side and the test load side are isolated at the boundary. The parameter adjustment layer performs temperature, pressure and humidity pre-processing on the gas entering the high-altitude environment simulation chamber. Combined with one-way isolation and pre-balancing and slow stop operation management, the target high-altitude background parameters are continuously established, input and maintained under the disturbance conditions of the wind tunnel operation in the chamber. The closed-loop control layer mainly consists of an industrial computer (23), a data acquisition card (31), a UWB wireless communication interface (29), and a control interface (30) for connecting with the wind tunnel system, parameter adjustment system, environmental homogenization components, and anti-condensation unit. As the integrated operation center of the environmental cabin body layer, the cabin wind tunnel layer, and the parameter adjustment layer, the closed-loop control layer implements cross-physical field linkage control of the wind tunnel system, the high-altitude parameter adjustment system, the environmental homogenization structure, and the anti-condensation unit. It performs coupled and coordinated control of the establishment and maintenance of the high-altitude background environment, the loading of local test airflow and the maintenance of flow field quality, and the supply and compensation of temperature, pressure, and humidity in the same time and space.

2. The cabin wind tunnel test platform-level system for high-altitude performance testing of aircraft components according to claim 1, characterized in that, The environmental cabin body layer is composed of multiple high-altitude environmental simulation cabins and cabin environment homogenization components. The cabin environment homogenization components include a temperature and humidity sensor array (2) and intelligent environmental homogenization fan array 1 (3) and intelligent environmental homogenization fan array 2 (16) arranged symmetrically inside the environmental cabin body (22). The temperature and humidity sensor array (2) is used to acquire temperature and humidity data of multiple spatial locations inside the environmental cabin body (22) in real time and calculate spatial temperature difference and humidity difference. The intelligent environmental homogenization fan array 1 (3) or intelligent environmental homogenization fan array 2 (16) performs start-stop or speed adjustment based on the comparison results of the spatial temperature difference and humidity difference with preset thresholds, and can actively suppress the macroscopic temperature and humidity gradient inside the cabin under the conditions of heat release, flow disturbance and humidity migration caused by the operation of the closed circulating wind tunnel inside the cabin.

3. The cabin wind tunnel test platform-level system for high-altitude performance testing of aircraft components according to claim 1, characterized in that, The in-cabin wind tunnel layer, as an embedded circulation subsystem, does not disrupt the overall stability of the low-pressure, low-temperature and humidity background environment inside the high-altitude environment simulation cabin when local airflow loads are applied. The sensors installed in the wind tunnel layer include a wind tunnel wind speed sensor (9). The wind tunnel wind speed sensor (9) is installed on the test section (11) and can measure the wind speed of the test section (11) and perform closed-loop correction on the wind tunnel fan (6). The wind tunnel fan (6) and the adjustable contraction section (7) form a dual actuator collaborative compensation structure. The speed of the adjustable contraction section (7) and the wind tunnel fan (6) are linked and adjusted, which can maintain the target wind speed and flow field stability of the test section (11) under the working condition of low air pressure leading to reduced gas density. The rectifier 1 (8) and rectifier 2 (12) are a composite rectification structure that together suppresses turbulence and improves flow velocity uniformity under low pressure, low temperature and variable humidity background conditions, providing stable, uniform and measurable local aerodynamic loading conditions for the test piece (10). The wind tunnel layer inside the cabin is also equipped with a wind tunnel wall temperature sensor (5), a wind tunnel gas temperature sensor (13), a wind tunnel humidity sensor (14), and a wind tunnel pressure sensor (15). When the wind tunnel inside the cabin is started, multiple sensors work together to monitor the wall temperature of the wind tunnel shell (24), the wind tunnel gas state parameters, and the drift of the operating conditions, which can support wind speed closed-loop correction and anti-condensation linkage control.

4. The cabin wind tunnel test platform-level system for high-altitude performance testing of aircraft components according to claim 1, characterized in that, In the parameter adjustment layer, the temperature control module (18), pressure control module (19) and humidity control module (20) work together on the same adjustment platform and jointly output the target temperature, pressure and humidity parameters; the temperature control module (18), pressure control module (19) and humidity control module (20) work together to form an integrated "temperature-pressure-humidity" pretreatment unit, which can coordinate the temperature, pressure and humidity of the working medium entering through the external clean gas input interface (28) before entering the high-altitude environment simulation chamber. The working medium immediately reaches the target low pressure, low temperature and set humidity state before entering the chamber, and at the same time establishes and continuously maintains the target high-altitude background parameters in the chamber. The temperature control module (18), pressure control module (19) and humidity control module (20) are connected in series along the flow direction of the external clean gas. The external clean gas input interface (28) is connected to the integrated "temperature-pressure-humidity" pretreatment unit to provide the high-altitude environment simulation chamber with clean gas that has been pretreated by temperature, pressure and humidity.

5. The cabin wind tunnel test platform-level system for high-altitude performance testing of aircraft components according to claim 1, characterized in that, In the closed-loop control layer, the industrial computer (23) accesses the multi-source sensor feedback signal through the data acquisition card (31) or the UWB wireless communication interface (29). The multi-source sensor feedback signal includes at least the wind speed signal of the wind tunnel wind speed sensor (9), the pressure signal of the wind tunnel pressure sensor (15), the spatial temperature and humidity distribution signal of the temperature and humidity sensor array (2), and the wall temperature signal of the wind tunnel wall temperature sensor (5). The industrial computer (23) implements cross-physical field linkage control of the wind tunnel fan (6) and adjustable shrink section (7) servo mechanism, temperature control module (18), pressure control module (19), humidity control module (20), intelligent environmental homogenizing fan array 1 (3), intelligent environmental homogenizing fan array 2 (16) and anti-condensation electric heating film (4) based on multi-source sensor feedback signals. Under the continuous operation disturbance of the wind tunnel in the cabin, it coordinates to maintain the target high-altitude background environmental parameters and the flow field stability of the test section, and performs time-series management of the entire process of pre-balancing, steady-state operation and slow stop reset. The industrial computer (23) incorporates wind speed, pressure, spatial distribution of temperature and humidity, and wall temperature as coupling variables into a unified judgment and unified adjustment framework to avoid the amplification of mutual disturbances caused by independent closed-loop control of temperature, pressure, humidity and wind speed.

6. The cabin wind tunnel test platform-level system for high-altitude performance testing of aircraft components according to claim 2, characterized in that, The temperature and humidity sensor array (2) is a multi-point distributed sensor array, including at least multiple sampling points located in the upper part, lower part and around the test section (11), which can identify the stratification of the cabin environment and local temperature and humidity drift. When starting, stopping or speed adjustment is performed, the temperature difference or humidity difference between any two sampling points of the temperature and humidity sensor array (2) exceeds the preset threshold as the trigger condition, so as to dynamically reduce and reshape the macroscopic temperature and humidity gradient in the cabin.

7. The cabin wind tunnel test platform-level system for high-altitude performance testing of aircraft components according to claim 2, characterized in that, The intelligent environment homogenizing fan array 1 (3) and the intelligent environment homogenizing fan array 2 (16) are non-continuously open fan arrays that start and stop and adjust speed according to thresholds, so as to reduce additional disturbances to the flow field of the wind tunnel test in the cabin and reduce energy consumption. The intelligent environment homogenizing fan array 1 (3) and the intelligent environment homogenizing fan array 2 (16) are arranged in vertical partitions along the height direction of the environmental cabin body (22) or symmetrically arranged relative to the center of the cabin body, forming a layered homogenizing flow field organization facing the layered environment inside the cabin.

8. The cabin wind tunnel test platform-level system for high-altitude performance testing of aircraft components according to claim 1, characterized in that, The parameter adjustment layer configures pre-balancing control strategies and easing control strategies; The pre-balance control strategy requires the environment to be established before the wind tunnel is started during the pre-balance stage. The parameter adjustment layer is configured with the pre-balance control strategy to adjust the air pressure, temperature and humidity in the chamber to the target value and maintain it stably for a preset time before starting the wind tunnel system in the chamber, so as to avoid the wind tunnel operation disturbance from interfering with the environment establishment stage. The slow-stop control strategy requires unloading the airflow before withdrawing the environment during the slow-stop phase. The parameter adjustment layer is configured with a slow-stop control strategy. At the end of the test, the airflow loading in the cabin wind tunnel is reduced and closed first, and then the temperature control module (18), pressure control module (19) and humidity control module (20) are delayed and closed to reduce the risk of pressure fluctuation, temperature and humidity drift and condensation caused by the shutdown transient.

9. The cabin wind tunnel test platform-level system for high-altitude performance testing of aircraft components according to claim 1, characterized in that, The industrial computer (23) has background field spatial consistency control and timing control of "pre-balance-steady state-stop". The industrial computer (23) takes the spatial consistency of the background environment field inside the cabin as an independent controlled target and calculates the temperature difference or humidity difference between any two sampling points based on the temperature and humidity sensor array (2). When the temperature difference or humidity difference exceeds the preset threshold, the intelligent environmental homogenization fan array is triggered to start, stop or speed is adjusted through the control interface (30) to actively reduce the macro temperature and humidity gradient in the cabin. The industrial computer (23) performs full-process timing control of pre-balancing, steady-state operation and slow stop reset. In the pre-balancing stage, the industrial computer (23) first controls the temperature control module (18), pressure control module (19) and humidity control module (20) to make the cabin environment reach and stabilize the target value before starting the cabin wind tunnel. In the slow stop reset stage, the industrial computer (23) first reduces and releases the wind tunnel airflow load and then delays the removal of temperature, pressure and humidity regulation to reduce the risk of transient disturbances during start-up and shutdown, temperature and humidity drift and condensation.

10. The cabin wind tunnel test platform-level system for high-altitude performance testing of aircraft components according to claim 1, characterized in that, The fluid connection method of the in-cabin wind tunnel test platform system is to form a hierarchical connection relationship in the system fluid path, namely "external air source pretreatment - environmental chamber background establishment - in-cabin wind tunnel closed circulation"; External clean gas enters the high-altitude parameter regulation system through the external clean gas input interface (28), and passes through the temperature control module (18), pressure control module (19) and humidity control module (20) in sequence along the flow direction to perform coordinated pretreatment of temperature, pressure and humidity on the working medium, so that the working medium reaches the preset high-altitude environmental parameter state before entering the high-altitude environment simulation chamber; The pre-treated working medium enters the high-altitude environment simulation chamber through a one-way valve (17) set between the high-altitude parameter adjustment system and the high-altitude environment simulation chamber, so as to establish a background environment of target temperature, target pressure and target humidity in the high-altitude environment simulation chamber; The enclosed wind tunnel test system is set up inside the high-altitude environment simulation chamber and forms an independent closed circulating airflow loop in the background environment, so that the working medium in the wind tunnel loop continues to circulate under the temperature, pressure and humidity conditions inside the chamber and does not directly exchange with the outside. The one-way valve (21) installed between the high-altitude parameter regulation system and the high-altitude environment simulation chamber can restrict the reverse flow of gas in the environment chamber towards the high-altitude parameter regulation system, and suppress the backflow interference caused by the low pressure and internal circulation conditions in the chamber to the parameter regulation side.

11. The cabin wind tunnel test platform-level system for high-altitude performance testing of aircraft components according to claim 1, characterized in that, The electrical signal connection method of the in-cabin wind tunnel test platform system is that each functional unit forms a unified monitoring-control network in terms of electrical connection and signal transmission. The industrial computer (23) serves as the core control node of the bidirectional coupled environmental dynamic control system. The data acquisition interface is simultaneously connected to the temperature and humidity sensor array, including at least the wind tunnel pressure sensor (15), the wind tunnel wind speed sensor (9), and the wind tunnel wall temperature sensor (5), so that the industrial computer (23) can obtain multi-source feedback quantities characterizing the high-altitude background environment, the flow field of the test section (11), and the thermal state of the wind tunnel wall. The control interface (30) is connected at least simultaneously to the servo mechanism of the wind tunnel fan (6), the adjustable retractable section (7), the temperature control module (18), the pressure control module (19), and the humidity control module (20) to achieve the linkage adjustment of the wind speed establishment of the test section (11) and the temperature, pressure, and humidity background establishment in the cabin within the same control framework; the industrial computer (23) is electrically connected to the temperature and humidity sensor array and can acquire the status signals of the temperature, humidity, air pressure, wind speed of the test section (11), and wall temperature of the wind tunnel shell (24) in real time in the high-altitude environment simulation cabin; The control interface (30) further connects the homogenizing fan array (3, 16) and the electric heating film (4) so ​​that the industrial computer (23) can simultaneously achieve the uniformity adjustment of temperature and humidity in the cabin and the anti-condensation protection of the wind tunnel shell (24) within the same monitoring-control network. The industrial computer (23) is electrically connected to the servo mechanism of the wind tunnel fan (6), the adjustable shrink section (7), the temperature control module (18), the pressure control module (19), the humidity control module (20), the electric heating film (4), and the homogenizing fan array (3, 16). Based on the status signal, it implements linkage adjustment of each execution unit to achieve unified control of wind speed maintenance, environmental parameter establishment, background field homogenization, and anti-condensation protection. The fully built-in wireless measurement and control support rod (25) set inside the test section (11) interacts with the industrial computer (23) via the UWB wireless communication protocol to exchange measurement data and control commands, so that the attitude adjustment signal and measurement data of the test piece (10) do not need to be transmitted through the cabin cable.

12. The cabin wind tunnel test platform-level system for high-altitude performance testing of aircraft components according to claim 1, characterized in that, The environmental establishment coupling link of the in-cabin wind tunnel test platform system includes a high-altitude parameter adjustment unit composed of a temperature control module (18), a pressure control module (19), and a humidity control module (20), which is used to implement integrated adjustment of temperature, pressure and humidity of the working medium entering the system; The adjusted working medium is input into the high-altitude environment simulation chamber through a one-way valve to provide the chamber with an environmental medium that meets the target working conditions. The high-altitude environment simulation chamber includes an environment chamber body (22) and an environment chamber body insulation layer (1). The environment chamber body (22) forms a closed space to contain the environmental medium. The environment chamber body insulation layer (1) is used to reduce heat exchange between the inside and outside of the chamber to maintain the stability of the temperature, pressure and humidity boundaries inside the chamber. The temperature and humidity sensor array (2) inside the chamber performs multi-point real-time detection of the temperature and humidity status at different locations inside the chamber to obtain spatial distribution information. Furthermore, when the temperature and humidity sensor array detects that the temperature or humidity deviation in any area exceeds the preset threshold, the intelligent environmental homogenizing fan array 1 (3) and the intelligent environmental homogenizing fan array 2 (16) operate under the scheduling of the control system to actively reduce and homogenize the macro temperature and humidity gradient inside the cabin.

13. The cabin wind tunnel test platform-level system for high-altitude performance testing of aircraft components according to claim 1, characterized in that, The cabin sealing and measurement coupling link of the cabin wind tunnel test platform system is that the test piece (10) is set in the test section (11) and mechanically supported by the fully built-in wireless measurement and control support rod (25); the fully built-in wireless measurement and control support rod (25) is set inside the high-altitude environment simulation cabin and located inside the test section (11) to perform attitude adjustment and aerodynamic response measurement of the test piece (10); the fully built-in wireless measurement and control support rod (25) integrates a six-dimensional force measurement unit (26) to acquire lift, drag, side force and torque signals; The fully built-in wireless measurement and control support rod (25) interacts with the external control system through a wireless communication protocol to exchange data and control commands, so that attitude adjustment signals and measurement data do not need to be transmitted through the cabin cable, thereby reducing the number of cabin penetration interfaces and reducing the risk of leakage under low pressure conditions; the UWB wireless communication protocol realizes the return of measurement data and the issuance of attitude adjustment commands through the UWB wireless communication interface (29). Furthermore, the high-altitude environment simulation chamber works together with the closed wind tunnel circuit inside the chamber through the isolation structure of one-way valve 1 (17) or one-way valve (21) to perform high-precision measurement of the attitude and aerodynamic response of the test piece (10) under the premise of maintaining the closed boundary conditions.

14. The cabin wind tunnel test platform-level system for high-altitude performance testing of aircraft components according to claim 1, characterized in that, The "pre-balancing-steady-state control-gradual shutdown" coupling link of the in-cabin wind tunnel test platform system is executed sequentially in the pre-balancing phase, steady-state control phase, and gradual shutdown phase during the test operation. During the pre-balancing phase, the high-altitude parameter adjustment system first establishes and adjusts the temperature, pressure and humidity inside the high-altitude environment simulation chamber, so that the environmental parameters inside the chamber reach the preset target value and remain stable for a predetermined time, while the wind tunnel system inside the chamber remains in an unactivated state. During the steady-state control phase, the wind tunnel system inside the cabin is started to operate, and the control system implements synchronous closed-loop adjustment of environmental parameters, wind speed in the test section (11), uniformity of the cabin environment and anti-condensation status, so that the background environmental field, local test flow field and anti-condensation protection are coordinated and maintained stably under the same working conditions. During the slow-down phase, the wind tunnel fan (6) is first decelerated to gradually release the test airflow load, and then the high-altitude parameter adjustment system is shut down after a delay to reduce the risk of sudden pressure changes, temperature and humidity drift and local condensation caused by the shutdown transient.

15. The in-cabin wind tunnel testing method for high-altitude aerodynamic coupling testing of aircraft components according to claim 1, applied to an in-cabin closed-loop wind tunnel testing system within a sealed high-altitude environment simulation cabin, characterized in that... Includes the following steps: S1. Set target operating conditions: Input the target wind speed, air pressure, temperature and relative humidity through the human-machine interface as the basis for subsequent control; S2. Environmental pre-equilibration: Before the test begins, environmental pre-equilibration is performed. Gas that has been conditioned for temperature, pressure and humidity is introduced into the environmental chamber through the high-altitude parameter adjustment system. The environmental parameters inside the chamber are adjusted to the target values ​​and stabilized for 10-30 minutes, so that the air pressure, temperature and humidity inside the environmental chamber reach the target working conditions. S3. Start the micro wind tunnel device and execute bidirectional coupling control: Start the wind tunnel layer inside the cabin and execute bidirectional coupling control. Adjust the speed of the wind tunnel fan (6) or the effective cross-sectional area of ​​the throat of the adjustable contraction section (7) according to the deviation between the actual wind speed and the target wind speed in the test section (11) to establish and maintain the target wind speed in the test section (11). At the same time, control the operation of the environmental homogenization fan array 1 (3) and the intelligent environmental homogenization fan array 2 (16) according to the uniformity of the cabin environment, and control the operation of the anti-condensation heating device according to the relationship between the wall temperature and the dew point temperature of the cabin air. S4. Real-time data acquisition: Real-time monitoring of cabin air pressure, temperature, relative humidity, wind tunnel gas state parameters, and wind tunnel shell wall temperature through various sensors installed inside the cabin, and collection of necessary feedback information; S5. Model testing: Under stable working conditions, the fully built-in wireless measurement and control support rod (25) completes the model angle of attack adjustment, and transmits the data of the six-dimensional force measurement unit (26) back to the computer (23) through the UWB wireless communication interface (29) to achieve high-precision measurement without cabin penetration; S6. Slow Stop and Reset: After the test, slow stop and reset are performed. First, gradually reduce the speed of the wind tunnel fan (6) to zero. After a delay of 2 minutes, shut down the high-altitude parameter adjustment system, and then shut down the environmental parameter control unit and auxiliary equipment to avoid pressure fluctuations or condensation problems in the cabin due to sudden shutdown.

16. The in-cabin wind tunnel test method for high-altitude aerodynamic coupling testing of aircraft components according to claim 15, characterized in that, Including S3. Starting the wind tunnel and executing bidirectional coupling control, the uniformity of the environmental space inside the cabin is monitored by an array of temperature and humidity sensors. When the temperature difference between any two points in the environmental cabin exceeds ±1℃ and the humidity difference exceeds ±5%RH, the intelligent environmental homogenization fan array is activated to improve the uniformity of the environment inside the cabin.

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