Multi-working-condition thermal management test system applied to aero-engine

Abstract

The invention discloses a multi-working-condition thermal management test system applied to an aero-engine, and relates to the technical field of engine tests. The test system comprises a thrust detection module which is used for detecting thrust data generated by the aero-engine during operation. The cooling simulation module compares difference data under the conditions of no acceleration and dynamic acceleration, the load adjustment module and the inertia compensation algorithm adjust the flow load and lag time of a cooling medium in real time through the difference data, and the load adjustment module controls the load adjustment module according to the difference data. According to the inertia compensation algorithm, the reaction time of equipment in the cooling device is adjusted based on the difference parameters, and the influence of inertia on the cooling device is simulated by adjusting the flow load and lag time of a cooling medium in real time, so that the obtained test data can adapt to thermal management requirements under different working conditions, and the test efficiency is improved. And the evaluation accuracy of the system performance is ensured.

Description

Technical Field

[0001] The invention relates to the technical field of engine testing, and in particular to a multi-operating-condition thermal management testing system applied to aircraft engines. Background Art

[0002] By simulating the thermal load of aircraft engines under different operating conditions, evaluating the performance of the thermal management system in terms of heat dissipation, heating, temperature control, etc., and testing the stability and reliability of the thermal management system under different operating conditions, it is ensured that the engine can operate safely and efficiently under various conditions. Based on the test results, the control strategy of the thermal management system is optimized to improve the system's heat dissipation capacity and work efficiency.

[0003] For example, the patent publication number "CN118310753A" is named "Semi-physical test system for thermal management of aircraft engines", which includes a monitoring interface, a simulator, a data transmission network and a physical entity; the simulator and the physical entity are connected through a data transmission network, the simulator includes a connected engine thermal management simulation model and a controller, and the physical entity includes a working fluid supply simulation device and a heat exchanger. The above invention realizes the digital transformation of the thermal management system of aircraft engines, which can reduce the risk and cost of thermal management tests of aircraft engines, shorten the development time, and provide an experimental basis for the study of thermal management systems of aircraft engines.

[0004] The above invention requires that when conducting thermal management tests on aircraft engines, the aircraft engines must be fixed in position and tested on the fixed aircraft engines. During actual flight, changes in the speed of the aircraft engines will affect changes in the airflow data outside the engine. At the same time, changes in the engine speed will cause the engine to be affected by changes in acceleration. When the engine is affected by changes in acceleration, the liquid cooling medium inside the cooling device inside the engine is also affected by inertia, which will affect the operation of the cooling device. During the test, since the aircraft engine is fixed, it is inconvenient for the cooling device to realize the influence of inertia on the cooling device. For this reason, a multi-condition thermal management test system for aircraft engines is invented. Summary of the invention

[0005] The purpose of the present invention is to provide a multi-condition thermal management test system for aircraft engines to solve the problems raised in the above background technology.

[0006] To achieve the above object, the present invention provides the following technical solution: a multi-condition thermal management test system for an aircraft engine, the test system comprising: Thrust detection module: The thrust detection module detects the thrust data generated by the aircraft engine during operation; Input module: The input module is used to control and detect the operating parameters of the aircraft engine; External simulation module: simulates the external data of the aircraft engine, including test airflow data, which includes natural airflow and relative airflow data; Information processing module: establishes a first correlation between relative airflow data, aircraft engine speed and airflow resistance through a correlation method, and the external simulation module adjusts the airflow data in the external simulation module based on the relative airflow data; Flight simulation module: obtain acceleration change data by simulating aircraft methods; Cooling simulation module: a cooling device model is established in a computer. The cooling device model performs cooling simulation without acceleration change to obtain basic operating parameters. The cooling device model performs cooling simulation in combination with acceleration change data to obtain simulated operating parameters of the cooling device model in acceleration change simulation. The difference data between the basic operating parameters and the simulated operating parameters is obtained by comparison method, and an inertia compensation algorithm is established. The inertia compensation algorithm obtains the lag time of adjusting the cooling device based on the difference parameters. Load adjustment module: The load adjustment module is installed in the cooling device. The load adjustment module is controlled by the simulation algorithm and the difference data to adjust the flow load of the cooling medium in the cooling device and adjust the reaction time of the equipment in the cooling device by the hysteresis time. General control module: realize the test under different working conditions through the general control method; Data monitoring and acquisition module: obtains the internal and external temperature data of the aircraft engine during the test and the cooling parameter data of the cooling device.

[0007] Furthermore, the aircraft simulation method includes: establishing a virtual model of the aircraft through a computer to obtain a virtual aircraft, inputting thrust data into the virtual aircraft to realize the operation of the virtual aircraft, obtaining speed data of the virtual aircraft, and adjusting the dynamic balance between the relative airflow data and the thrust data through a balance adjustment method, and obtaining acceleration change data based on the movement data.

[0008] Furthermore, the cooling simulation module includes: A virtual model of the cooling device is established by computer modeling technology, and the virtual model can simulate the equipment in the cooling device; In the virtual model, the cooling device is simulated through acceleration change data to simulate the dynamic changes of the aircraft in different flight phases and acceleration conditions in actual flight; The flow of the cooling medium in the cooling device is simulated by using acceleration change data, and the inertial effect in the cooling medium is analyzed. The inertial effect includes the flow velocity, pressure distribution and flow load of the cooling medium.

[0009] Furthermore, the association method includes obtaining a second association between relative airflow data and the virtual aircraft speed in the external data, obtaining a third association between airflow resistance and aircraft engine speed, and combining the second association data and the third association data to obtain a first association between the relative airflow data, aircraft engine speed data and resistance.

[0010] Furthermore, the simulation algorithm includes: obtaining a load adjustment strategy based on the difference data simulation, and the load adjustment strategy is applied to adjust the load parameters in the load adjustment module; The method for obtaining the load adjustment strategy includes: adjusting the internal parameters of the load adjustment module according to the difference data by a simulation algorithm, simulating and controlling the parameters of the load adjustment module to change, achieving that the operating state of the cooling device without inertia is equal to the operating state of the cooling device under the corresponding inertia, recording the changed parameters in the load adjustment module, and obtaining the load adjustment strategy.

[0011] Furthermore, the overall control method includes: controlling the input parameters in the input module, simulating the speed data of the virtual aircraft to realize flying under different working conditions, obtaining relative airflow data in combination with the No. 1 association, the external simulation module adjusting the device inside the external simulation module based on the relative airflow data, the cooling device adjusting the lag time of the cooling device and adjusting the load adjustment module according to the difference data, and the data monitoring and acquisition module obtaining the internal and external temperature data of the aircraft engine in the test and the cooling parameter data of the cooling device in real time.

[0012] Furthermore, the inertia compensation algorithm includes: quantifying the lag effect of the acceleration change data on the flow of the cooling medium by a second-order differential equation to obtain the lag time; The reaction time of the equipment in the cooling device is adjusted by the hysteresis time, the operation of the cooling device under actual working conditions is simulated using the cooling device model and the hysteresis time, and the reaction time of the equipment in the cooling device is measured.

[0013] Furthermore, the comparison method includes: Selecting comparison indicators according to the application scenario of the cooling device and the requirements of load adjustment, wherein the comparison indicators include the flow load difference, temperature change difference and pressure change difference of the cooling medium; Point-by-point comparison: compare the basic operating parameters and simulated operating parameters point-by-point according to the time points, and analyze the differences in the comparison indicators at each time point under each working condition; Trend analysis: Analyze the overall change trend of the comparison indicators in the basic operating parameters and simulated operating parameters; Difference degree assessment: Calculate and obtain the difference data between the basic operating parameters and the simulated operating parameters based on the difference situation and overall change trend.

[0014] Compared with the prior art, the present invention has the following beneficial effects: In the multi-operating condition thermal management test system applied to aircraft engines, the cooling simulation module compares the difference data under no acceleration and dynamic acceleration, the load adjustment module and the inertia compensation algorithm adjust the load and lag time of the cooling medium flow in real time through the difference data, the load adjustment module controls the load adjustment module according to the difference data, and the inertia compensation algorithm adjusts the reaction time of the equipment in the cooling device based on the difference parameters, and simulates the influence of inertia on the cooling device by adjusting the load and lag time of the cooling medium flow in real time, so that the acquired test data can adapt to the thermal management requirements under different operating conditions, and ensure the accuracy of the system performance evaluation.

[0015] At the same time, the external simulation module is used to combine the natural airflow and relative airflow data for simulation, dynamically simulate the operation under different flight conditions, simulate the influence of airflow on aircraft engines under complex real conditions, and based on the virtual aircraft model and balance adjustment method of the flight simulation module, the actual thrust data and the acceleration changes of the virtual aircraft are linked in real time, and the dynamic balance of thrust and airflow data is automatically adjusted, which significantly improves the accuracy of matching the engine thrust output with the flight status.

[0016] The external simulation module combines natural airflow and relative airflow data for comprehensive simulation, and can dynamically reproduce the operating environment of aircraft engines under different flight conditions. This simulation not only improves the accuracy of the test, but also helps to deeply understand the thermal load of aircraft engines under different airflow environments during actual flight, and then obtain internal and external temperature data and cooling parameter data for subsequent optimization of thermal management system control strategies. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 A schematic diagram for calculating inertial effects for the present invention; Figure 2 A schematic diagram of a cooling device in an adjustment test of the present invention; Figure 3 Schematic diagram of the test system of the present invention. DETAILED DESCRIPTION

[0018] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0019] like Figure 1 - Figure 3As shown, the present invention provides a technical solution: a multi-condition thermal management test system for an aircraft engine, the test system comprising: Thrust detection module: The thrust detection module detects the thrust data generated by the aircraft engine during operation; Input module: The input module is used to control and detect the operating parameters of the aircraft engine; External simulation module: simulates the external data of the aircraft engine, including test airflow data, which includes natural airflow and relative airflow data; Information processing module: establishes a first correlation between relative airflow data, aircraft engine speed and airflow resistance through a correlation method, and the external simulation module adjusts the airflow data in the external simulation module based on the relative airflow data; Flight simulation module: obtain acceleration change data by simulating aircraft methods; Cooling simulation module: a cooling device model is established in a computer. The cooling device model performs cooling simulation without acceleration change to obtain basic operating parameters. The cooling device model performs cooling simulation in combination with acceleration change data to obtain simulated operating parameters of the cooling device model in acceleration change simulation. The difference data between the basic operating parameters and the simulated operating parameters is obtained by comparison method, and an inertia compensation algorithm is established. The inertia compensation algorithm obtains the lag time of adjusting the cooling device based on the difference parameters. Load adjustment module: The load adjustment module is installed in the cooling device. The load adjustment module is controlled by the simulation algorithm and the difference data to adjust the flow load of the cooling medium in the cooling device and adjust the reaction time of the equipment in the cooling device by the hysteresis time. General control module: realize the test under different working conditions through the general control method; Data monitoring and acquisition module: obtains the internal and external temperature data of the aircraft engine during the test and the cooling parameter data of the cooling device.

[0020] The aircraft simulation method includes: establishing a virtual model of the aircraft through a computer to obtain a virtual aircraft, inputting thrust data into the virtual aircraft to realize the operation of the virtual aircraft, obtaining speed data of the virtual aircraft, and adjusting the dynamic balance between relative airflow data and thrust data through a balance adjustment method, and obtaining acceleration change data based on movement data.

[0021] The cooling simulation module includes: A virtual model of the cooling device is established by computer modeling technology, and the virtual model can simulate the equipment in the cooling device; In the virtual model, the cooling device is simulated through acceleration change data to simulate the dynamic changes of the aircraft in different flight phases and acceleration conditions in actual flight; The flow of the cooling medium in the cooling device is simulated by using acceleration change data, and the inertial effect in the cooling medium is analyzed. The inertial effect includes the flow velocity, pressure distribution and flow load of the cooling medium.

[0022] The correlation method includes obtaining a second correlation between relative airflow data and the virtual aircraft speed in the external data, obtaining a third correlation between airflow resistance and aircraft engine speed, and combining the second correlation data and the third correlation data to obtain a first correlation between relative airflow data, aircraft engine speed data and resistance.

[0023] The simulation algorithm includes: obtaining a load adjustment strategy based on the difference data simulation, and the load adjustment strategy is applied to adjust the load parameters in the load adjustment module; The method for obtaining the load adjustment strategy includes: adjusting the internal parameters of the load adjustment module according to the difference data by a simulation algorithm, simulating and controlling the parameters of the load adjustment module to change, achieving that the operating state of the cooling device without inertia is equal to the operating state of the cooling device under the corresponding inertia, recording the changed parameters in the load adjustment module, and obtaining the load adjustment strategy.

[0024] The overall control method includes: controlling the input parameters in the input module, simulating the speed data of the virtual aircraft to realize the flight under different working conditions, combining the No. 1 association to obtain the relative airflow data, the external simulation module adjusts the device inside the external simulation module based on the relative airflow data, the cooling device adjusts the lag time of the cooling device and adjusts the load adjustment module according to the difference data, and the data monitoring and acquisition module obtains the internal and external temperature data of the aircraft engine in the test and the cooling parameter data of the cooling device in real time.

[0025] The inertia compensation algorithm includes: quantifying the hysteresis effect of acceleration change data on the flow of cooling medium through a second-order differential equation to obtain the hysteresis time; The reaction time of the equipment in the cooling device is adjusted by the hysteresis time, the operation of the cooling device under actual working conditions is simulated using the cooling device model and the hysteresis time, and the reaction time of the equipment in the cooling device is measured.

[0026] The comparison methods include: Select comparison indicators based on the application scenario of the cooling device and the requirements of load adjustment. The comparison indicators include the flow load difference, temperature change difference and pressure change difference of the cooling medium; Point-by-point comparison: compare the basic operating parameters and simulated operating parameters point-by-point according to the time points, and analyze the differences in the comparison indicators at each time point under each working condition; Trend analysis: Analyze the overall change trend of the comparison indicators in the basic operating parameters and simulated operating parameters; Difference degree assessment: Calculate and obtain the difference data between the basic operating parameters and the simulated operating parameters based on the difference situation and overall change trend.

[0027] When conducting thermal management tests on aircraft engines under multiple operating conditions, the aircraft engines need to be fixed in position. The thrust detection module detects the thrust data generated by the aircraft engines under different operating conditions while fixing the position of the aircraft engines. The thrust data is obtained by detecting the thrust generated by the aircraft engines during operation. The thrust data is substituted into the simulated aircraft to obtain the acceleration change data of the simulated aircraft under different operating conditions based on the thrust data.

[0028] The multi-operating conditions of the engine refer to processes such as take-off, climb and landing. The specific content of the multi-operating conditions is the existing technology. During this process, the acceleration of the engine will change. The process of acceleration change includes acceleration, deceleration and change of moving direction. Inertia refers to the property of an object to maintain a stationary state or a uniform linear motion state. In the process of acceleration change, the inertia inside the engine will affect thermal management.

[0029] The external simulation module is the basic part of this system. Its main function is to simulate the airflow and temperature conditions of aircraft engines in actual environments. By controlling parameters such as airflow speed, direction and temperature, the working environment of aircraft engines under different flight altitudes, speeds and climatic conditions can be simulated. This helps to more realistically reflect the thermal load of aircraft engines during actual flight and provide an accurate environmental basis for subsequent thermal management performance tests. At the same time, considering that the position of the aircraft engine is fixed in the test, while in reality, the aircraft engine is in a moving state, the external simulation module needs to consider the relative airflow data of the aircraft engine relative to the external airflow in the test when controlling the airflow speed. Through the thrust data of the aircraft engine, the impact on the virtual aircraft is simulated to obtain the movement data of the aircraft, and the relative airflow data is obtained based on the movement data of the aircraft. Natural airflow refers to the airflow condition in the natural environment. When in use, a natural airflow environment can be designed to simulate thermal management tests under different working conditions and different natural airflow environments. The test airflow data includes natural airflow and relative airflow data. The relative airflow data is controlled by the speed of the simulated aircraft, and the natural airflow refers to the natural airflow condition in the outside world.

[0030] Through the relative airflow data and movement data, the movement data is corrected to obtain the theoretical movement data. The relative airflow data will affect the movement data of the virtual aircraft, and the movement data will also affect the relative airflow data. The two will affect each other, so as to obtain the No. 2 correlation between the relative airflow data and the virtual aircraft speed in the external data. There will also be airflow resistance in the movement process, and the No. 3 correlation between the airflow resistance and the aircraft engine speed is obtained. The No. 2 correlation and the No. 3 correlation are combined to obtain the No. 1 correlation between the relative airflow data, the aircraft engine speed data and the resistance. The movement data is combined with time to obtain the acceleration change data. While recording the data, the system will also record the corresponding time.

[0031] The acceleration change data acts on the cooling device and will affect the cooling medium in the cooling device. Since the position of the aircraft engine is fixed in the test, the lack of inertia will not affect the cooling device in the test. However, in actual situations, the existence of inertia will affect the cooling device. Acceleration changes can affect the flow state of the cooling medium. In the cooling system, the flow characteristics of the cooling medium are crucial to the heat transfer effect. When the acceleration changes, the flow rate, flow direction and flow state of the cooling medium may change, thereby affecting its heat transfer performance. Therefore, it is necessary to simulate the impact of acceleration changes on the cooling device in the test, and simulate the impact of acceleration changes on the cooling device and thermal management in actual situations. The cooling device cools the key parts of the engine.

[0032] The input module is responsible for controlling the operating parameters of the aircraft engine under different working conditions to simulate the input parameters under different actual working conditions. By controlling key parameters such as the aircraft engine's fuel supply, intake pressure, and speed, it can simulate the aircraft engine's working state under different working conditions such as take-off, climb, cruise, descent, and landing.

[0033] The operating method of the test system includes controlling the aircraft engine through the input module to start the aircraft engine, controlling the operating parameters through the input module to start the aircraft engine, generating thrust during the start-up process of the aircraft engine, detecting thrust data by the thrust detection module, and realizing simulated flight of the virtual aircraft based on the thrust data by the virtual model of the aircraft. Meanwhile, during the simulated flight, the natural airflow is designed in advance, and during the movement of the virtual aircraft, relative airflow data is obtained based on the moving speed and simulated altitude of the virtual aircraft. The relative airflow data is combined with the natural airflow to obtain test airflow data, and the external simulation module adjusts the external airflow data of the aircraft engine in the test through the test airflow data, and realizes the thermal correlation test under different natural airflows by designing different natural airflows.

[0034] The cooling device includes the lubricating oil system in the aircraft engine. The lubricating oil system transfers the absorbed heat to the cooling devices such as the lubricating oil radiator outside the engine through circulation. After heat dissipation, the cooled lubricating oil is returned to the engine, thereby maintaining the temperature of each component inside the engine within an appropriate range and ensuring the stability of engine performance. The lubricating oil system is also used to assist the engine in heat dissipation in thermal management. The thermal management test system comprehensively detects the thermal response capability and performance of the aircraft engine cooling device, which can provide an important basis for the thermal management design of the aircraft engine, optimize the structure and parameter settings of the thermal management system, and improve the overall performance of the engine.

[0035] Due to the existence of inertia in actual flight, the liquid cooling medium in the engine cooling device, especially the cooling device using liquid as the cooling medium, is affected by inertia during the acceleration change in the actual flight. The liquid cooling medium in the cooling device is affected by inertia and thus affects the cooling effect of the cooling device. The thrust data generated by the aircraft engine under different working conditions and the operating parameters of the aircraft engine under different working conditions are obtained. The thrust data and the test airflow data are applied to the virtual aircraft to obtain movement data. The movement data is combined with the actual to obtain the acceleration data of the virtual aircraft.

[0036] The comparison method includes point-by-point comparison, trend analysis and difference evaluation methods to comprehensively analyze the difference data in the cooling system. The difference data includes flow load and pressure, providing a scientific basis for the load adjustment strategy. By analyzing the difference data and adjusting the flow load in the cooling device, the pressure and flow load inside the cooling medium in the cooling device can be close to the data in the simulated operation parameters. The load adjustment module operates according to the load adjustment strategy. The cooling device adjusts the response time of the equipment in the cooling device through the lag time. The load adjustment module simulates the operation of the cooling device under inertia by adjusting the flow load of the cooling medium in the cooling device and the response time of the equipment in the cooling device. Based on the simulation of the operation of the cooling device under inertia, the corresponding thermal management data is obtained in the test. The data about the cooling device can be more consistent with the operation of the cooling device under actual flight, providing effective support for the utilization of subsequent test data and the optimization of the thermal management system.

[0037] For the cooling device in thermal management, inertia will affect the cooling medium of the cooling device. Since the cooling medium itself has inertia, especially the liquid cooling medium, during the acceleration stage, the liquid cooling medium will affect the operation of the cooling device due to inertia. The flow rate and pressure distribution changes of the liquid cooling medium will directly affect the heat transfer coefficient. During the acceleration stage, due to the uneven distribution of flow rate and pressure, the heat transfer coefficient may change, thereby affecting the cooling efficiency. Due to the inertia of the liquid, there may be a delay in the corresponding temperature change of the cooling medium. This delay will cause the cooling device to perform poorly when dealing with sudden heat loads. Therefore, inertia will affect the thermal management performance of the cooling device. The influence is especially for cooling devices that use liquid cooling media. Since the mass of the liquid cooling medium is larger, its inertia is also greater. When the liquid cooling medium changes in temperature, energy transfer and conversion are required inside it. Due to the effect of inertia, this energy transfer and conversion process will not be completed immediately, but requires a certain amount of time. This causes a delay in the coolant's response to temperature changes. When the coolant needs to change the flow rate to respond to temperature changes, due to the effect of inertia, the change in flow rate will not occur immediately. This delay in flow rate change will further affect the temperature response speed of the coolant. Due to the effect of inertia, the temperature response of the coolant is delayed, resulting in reduced heat dissipation efficiency.

[0038] By combining the movement data with time, the acceleration change data under different working conditions are obtained, and the acceleration change is applied to the cooling simulation module to perform simulations without inertia and with inertia. Since it is a computer simulation, both simulations can be achieved by adjusting the parameters inside the computer during the simulation. The simulation without inertia corresponds to the operation of the cooling device inside the aircraft engine during the test. During the test of the aircraft engine, the position of the aircraft engine is fixed, so there is no inertia affecting the cooling device. The cooling device model combines the acceleration change data to perform cooling simulation, which corresponds to the actual operation of the cooling device inside the aircraft engine. During the operation, inertia affects the cooling device. The difference data between the basic operating parameters and the simulated operating parameters are obtained by comparison. Based on the difference data, the operation of the cooling device in the test is used to simulate the actual operation of the cooling device. The flow load of the cooling medium in the cooling device is adjusted through the load adjustment module, and the reaction time of the equipment in the cooling device is adjusted through the lag time. In this way, it can be ensured that the cooling device can simulate the operation under actual conditions and the influence of inertia in the test. The external simulation module is combined with the natural airflow and relative airflow data for simulation, and the operation under different flight conditions is dynamically simulated. The influence of airflow on aircraft engines under complex real conditions is simulated. Based on the virtual aircraft model and balance adjustment method of the flight simulation module, the actual thrust data is linked to the acceleration changes of the virtual aircraft in real time, and the dynamic balance of thrust and airflow data is automatically adjusted, which significantly improves the accuracy of matching the engine thrust output with the flight state.

[0039] The hysteresis effect of the cooling medium flow can be regarded as the second-order dynamic response of the acceleration change. When the cooling medium (such as liquid lubricating oil) changes in acceleration, the inertia effect will cause dynamic hysteresis in the flow velocity, pressure distribution and flow load. When the aircraft accelerates, the liquid medium tends to maintain its original state due to inertia, resulting in a delay in flow velocity adjustment, which in turn affects the heat dissipation efficiency. The second-order differential equation is used to describe the dynamic effect of inertia on the cooling medium. The equation may be in the form of: , where m represents the equivalent inertial mass of the cooling medium, c is the damping coefficient (reflecting the flow resistance), k is the stiffness coefficient (reflecting the elasticity of the medium), F(t) is the dynamic force caused by the acceleration change, and x is the displacement of the cooling medium. By solving this equation, the hysteresis response of the cooling medium flow rate, pressure and other parameters can be quantified, the time domain response of the flow rate can be obtained, and the lag time t can be extracted. The lag time R represents the adjustment ability of the cooling device to the acceleration change, which is inversely proportional to the lag time t. The reaction time refers to the time difference between the actuator (such as valve, pump) in the cooling device from receiving the control signal to the actual action. The inertial effect will prolong this time, resulting in control delay. Through the cooling device model and the lag time The operation of the cooling device under actual working conditions is simulated, and the reaction time of the equipment in the cooling device is measured. The cooling simulation module compares the difference data under no acceleration and dynamic acceleration. The load adjustment module and the inertia compensation algorithm adjust the load and lag time of the cooling medium flow in real time through the difference data. The load adjustment module controls the load adjustment module according to the difference data. The inertia compensation algorithm adjusts the reaction time of the equipment in the cooling device based on the difference parameters. The load and lag time of the cooling medium flow are adjusted in real time to simulate the influence of inertia on the cooling device, so that the acquired test data can adapt to the thermal management requirements under different working conditions, thereby ensuring the accuracy of the system performance evaluation.

[0040] The test airflow data is considered to be a combination of natural airflow and relative airflow data. Under different working conditions, the natural airflow and engine movement data have not changed. The relative airflow data is affected by the movement data. At the same time, the test airflow data will affect the thrust data. Therefore, the test airflow data and speed data are combined, and simulated flight is carried out through a virtual aircraft to obtain movement data.

[0041] The dynamic balance between the relative airflow data and the thrust data is adjusted by a balance adjustment method, wherein when the engine is running to generate thrust, the thrust data is input into the virtual aircraft, causing the virtual aircraft to start moving. When the virtual aircraft starts to move, the relative airflow data starts to change from zero. When the virtual aircraft is stationary, the relative airflow data is zero, indicating that there is no relative airflow data at this time. Changes in the relative airflow data will have an impact on the virtual aircraft. At this time, in order to ensure the smooth operation of the virtual aircraft, the thrust data will be adjusted to ensure the speed of the virtual aircraft. The speed will affect the relative airflow data, and the thrust data will affect the speed. Therefore, the relative airflow data and the thrust data achieve a dynamic balance between the two in the process of mutual influence. The thrust data is controlled by the operating parameters of the aircraft engine, and the operation of the virtual aircraft is achieved through the dynamic balance between the two.

[0042] The cooling parameter data includes the heat absorption data after cooling, the number of cycles and the temperature change of the cooling medium. The internal and external temperature data of the engine under different working conditions can provide an important basis for the thermal management design of the aircraft engine, help engineers identify potential thermal management problems, optimize the structure and parameter settings of the thermal management system, and improve the overall performance of the engine. The internal and external temperature data of the engine under different working conditions include various systems inside the engine, which include thermal management related components such as the aircraft engine cooling system, lubrication system, and thermal protection system. After obtaining the internal and external temperature data, the internal and external temperature data can be divided according to the system or component to facilitate subsequent processing. According to the test results, the control strategy of the thermal management system is optimized to improve the heat dissipation capacity and work efficiency of the system. Through adaptive control technology, the thermal management system can automatically adjust the working mode according to different flight conditions and select the best thermal management path. The external simulation module combines natural airflow and relative airflow data for comprehensive simulation, which can dynamically reproduce the operating environment of the aircraft engine under different flight conditions. This simulation not only improves the accuracy of the test, but also helps to deeply understand the thermal load of the aircraft engine under different airflow environments in actual flight, and then can obtain the internal and external temperature data and cooling parameter data for subsequent optimization of the thermal management system control strategy.

[0043] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is limited by the attached embodiments and their equivalents.

Claims

1. A multi-condition thermal management test system for aircraft engines, characterized by: The test system comprises: Thrust detection module: The thrust detection module detects the thrust data generated by the aircraft engine during operation; Input module: The input module is used to control and detect the operating parameters of the aircraft engine; External simulation module: simulates the external data of the aircraft engine, including test airflow data, which includes natural airflow and relative airflow data; Information processing module: establishes a first correlation between relative airflow data, aircraft engine speed and airflow resistance through a correlation method, and the external simulation module adjusts the airflow data in the external simulation module based on the relative airflow data; Flight simulation module: obtain acceleration change data by simulating aircraft methods; Cooling simulation module: a cooling device model is established in a computer. The cooling device model performs cooling simulation without acceleration change to obtain basic operating parameters. The cooling device model performs cooling simulation in combination with acceleration change data to obtain simulated operating parameters of the cooling device model in acceleration change simulation. The difference data between the basic operating parameters and the simulated operating parameters is obtained by comparison method, and an inertia compensation algorithm is established. The inertia compensation algorithm obtains the lag time of adjusting the cooling device based on the difference parameters. Load adjustment module: The load adjustment module is installed in the cooling device. The load adjustment module is controlled by the simulation algorithm and the difference data to adjust the flow load of the cooling medium in the cooling device and adjust the reaction time of the equipment in the cooling device by the hysteresis time. General control module: realize the test under different working conditions through the general control method; Data monitoring and acquisition module: obtains the internal and external temperature data of the aircraft engine during the test and the cooling parameter data of the cooling device.

2. The multi-condition thermal management test system for aircraft engines according to claim 1, characterized in that: The aircraft simulation method comprises: establishing a virtual model of the aircraft by a computer to obtain a virtual aircraft, inputting thrust data into the virtual aircraft to realize the operation of the virtual aircraft, obtaining speed data of the virtual aircraft, and adjusting the dynamic balance between the relative airflow data and the thrust data by a balance adjustment method, and obtaining acceleration change data based on movement data.

3. The multi-condition thermal management test system for aircraft engines according to claim 1, characterized in that: The cooling simulation module includes: A virtual model of the cooling device is established by computer modeling technology, and the virtual model can simulate the equipment in the cooling device; In the virtual model, the cooling device is simulated through acceleration change data to simulate the dynamic changes of the aircraft in different flight phases and acceleration conditions in actual flight; The flow of the cooling medium in the cooling device is simulated by using acceleration change data, and the inertial effect in the cooling medium is analyzed. The inertial effect includes the flow velocity, pressure distribution and flow load of the cooling medium.

4. The multi-condition thermal management test system for aircraft engines according to claim 1, characterized in that: The association method includes obtaining a second association between relative airflow data and a virtual aircraft speed in external data, obtaining a third association between airflow resistance and aircraft engine speed, and combining the second association data and the third association data to obtain a first association between relative airflow data, aircraft engine speed data and resistance.

5. The multi-condition thermal management test system for aircraft engines according to claim 1, characterized in that: The simulation algorithm includes: obtaining a load adjustment strategy based on the difference data simulation, and the load adjustment strategy is applied to adjust the load parameters in the load adjustment module; The method for obtaining the load adjustment strategy includes: adjusting the internal parameters of the load adjustment module according to the difference data by a simulation algorithm, simulating and controlling the parameters of the load adjustment module to change, achieving that the operating state of the cooling device without inertia is equal to the operating state of the cooling device under the corresponding inertia, recording the changed parameters in the load adjustment module, and obtaining the load adjustment strategy.

6. The multi-condition thermal management test system for aircraft engines according to claim 4, characterized in that: The overall control method includes: controlling input parameters in the input module, simulating the speed data of the virtual aircraft to realize flight under different working conditions, obtaining relative airflow data in combination with the first association, the external simulation module adjusting the device inside the external simulation module based on the relative airflow data, the cooling device adjusting the lag time of the cooling device and adjusting the load adjustment module according to the difference data, and the data monitoring and acquisition module obtaining the internal and external temperature data of the aircraft engine in the test and the cooling parameter data of the cooling device in real time.

7. The multi-condition thermal management test system for aircraft engines according to claim 1, characterized in that: The inertia compensation algorithm includes: quantifying the lag effect of acceleration change data on the flow of cooling medium through a second-order differential equation to obtain the lag time; The reaction time of the equipment in the cooling device is adjusted by the hysteresis time, the operation of the cooling device under actual working conditions is simulated using the cooling device model and the hysteresis time, and the reaction time of the equipment in the cooling device is measured.

8. The multi-condition thermal management test system for aircraft engines according to claim 1, characterized in that: The comparison method includes: Selecting comparison indicators according to the application scenario of the cooling device and the requirements of load adjustment, wherein the comparison indicators include the flow load difference, temperature change difference and pressure change difference of the cooling medium; Point-by-point comparison: compare the basic operating parameters and simulated operating parameters point-by-point according to the time points, and analyze the differences in the comparison indicators at each time point under each working condition; Trend analysis: Analyze the overall change trend of the comparison indicators in the basic operating parameters and simulated operating parameters; Difference degree assessment: Calculate and obtain the difference data between the basic operating parameters and the simulated operating parameters based on the difference situation and overall change trend.

Images