A general research model of complex flow in a flying wing aircraft with wide-range Reynolds number and internal-external flow coupling

Abstract

This application belongs to the field of wind tunnel test model design and discloses a general research model for complex Reynolds number flow with internal and external flow coupling in a flying wing aircraft. The general research model for complex Reynolds number flow with internal and external flow coupling in a flying wing aircraft includes: a nose section, an air inlet lip section, a fuselage upper cover, a fuselage lower cover, a leading-edge flap section, a tail nozzle section, and a fuselage main body. The fuselage main body integrates the mounting interfaces for the nose section, air inlet lip section, fuselage upper cover, fuselage lower cover, leading-edge flap section, and tail nozzle section. Furthermore, the fuselage main body is internally designed with an internal flow channel, a measuring balance mounting interface, and reserved sensor mounting positions. This application's model features modularity, versatility, sloping underbody support, and adaptability to extreme environments.

Description

Technical Field

[0001] This application belongs to the field of wind tunnel test model design, and in particular relates to a general research model for complex Reynolds number flow with wide-range coupling of internal and external flows in a flying wing configuration aircraft. Background Technology

[0002] General-purpose wind tunnel test models are important tools for studying the aerodynamic characteristics and analyzing the flow field characteristics of aircraft. Their main functions are to verify the accuracy of numerical simulation methods; secondly, general-purpose test models can be used to study the basic aerodynamic performance of aircraft with typical layouts, laying the foundation for aircraft design optimization; finally, wind tunnel test models can also be used to study complex flow mechanisms and verify the quality of wind tunnel flow fields, ensuring the authenticity and reliability of experimental results.

[0003] Low-aspect-ratio flying wing aircraft, as a typical aerodynamic configuration, have been widely used in the design of many aircraft. Therefore, understanding the basic aerodynamic characteristics of this type of aircraft is crucial for optimizing the aerodynamic layout of advanced flying wing aircraft and improving their performance.

[0004] However, the commonly used general research models for low-aspect-ratio flying wing aircraft have significant limitations. These models are often oversimplified, based solely on a simple delta wing form. While such models can simulate the leading-edge vortex structure and related aerodynamic characteristics of delta wing aircraft, simplifying the study of flow complexity, for real aircraft, not only is fuselage thickness affected, but the shape characteristics of external components such as the propulsion system and air intake also significantly influence their overall aerodynamic performance. More importantly, the study of the coupling characteristics between internal and external flows is a crucial issue in flying wing aircraft research. Currently, most studies are limited to simulating the fuselage or air intake alone, lacking a general research model that can simultaneously consider the coupling effects of internal and external flows.

[0005] Therefore, for low aspect ratio flying wing aircraft, inventing a general research model that can comprehensively consider external characteristics such as fuselage thickness and propulsion system shape, and simultaneously simulate the coupling effect of internal and external flows, has important theoretical significance and practical application value. Summary of the Invention

[0006] The purpose of this application is to overcome the problems of the prior art and disclose a general research model for complex Reynolds number flow with internal and external flow coupling in a flying wing configuration aircraft. The model of this application has many features such as modularity, generality, oblique support and adaptability to extreme environments.

[0007] The objective of this application is achieved through the following technical solution:

[0008] A general research model for complex Reynolds number flows involving internal and external flows of a flying wing aircraft, comprising:

[0009] The nose section, air intake lip section, upper fuselage cover, lower fuselage cover, leading edge flap section, tail nozzle section, and main fuselage body.

[0010] The main body of the fuselage integrates the mounting interfaces for the head assembly, air intake lip assembly, upper fuselage cover, lower fuselage cover, leading edge flap assembly, and tail nozzle assembly. The main body of the fuselage is also designed with an internal flow channel, a measuring balance mounting interface, and reserved sensor mounting positions.

[0011] According to a preferred embodiment, the general research model for complex wide-domain Reynolds number flows involving internal and external flow coupling in flying wing aircraft further includes a sloping support structure.

[0012] The inclined support structure includes a support rod for connecting and fixing the research model. The support rod has a V-structure design and an interface adapted to the support rod is provided on the main body of the fuselage.

[0013] One end of the support rod is connected to the measuring balance via an inner conical hole, and the other end is connected to the cavity mechanism via a cylindrical surface and tightened with screws.

[0014] According to a preferred embodiment, the nose section includes the head shape structure of a flying wing aircraft, and the nose section integrates an acceleration sensor mounting interface.

[0015] The nose section is manufactured using CNC machining according to the geometric parameters of the flying wing layout, and is equipped with an adapter interface for connection with the main fuselage.

[0016] According to a preferred embodiment, the head assembly and the main body are fitted with a shaft hole, and positioned by a pin and tightened by screws.

[0017] According to a preferred embodiment, the intake lip component is modularly designed, supporting either a plugging cone configuration or a ventilation configuration, and the intake lip type can be selected according to test requirements.

[0018] Blocking cone configuration: Install a blocking cone component at the inlet of the air intake to isolate the internal flow, so as to facilitate independent study of the external flow field characteristics;

[0019] Ventilation configuration: The ventilation lip component design allows the internal and external flow fields to interact, simulating the coupling effect of a real aircraft.

[0020] According to a preferred embodiment, the upper cover plate and the lower cover plate are detachable modules, and the upper cover plate and the lower cover plate have reserved sensor mounting slots inside to complete the arrangement and installation of pressure measuring hoses and pulsating pressure sensor equipment in the experiment.

[0021] According to a preferred embodiment, the leading edge flap component supports the configuration of flaps with different deflection angles; the leading edge flap component is manufactured according to the leading edge geometry parameters of the flying wing layout and is designed with an adapter interface to achieve rapid switching of different deflection angles.

[0022] According to a preferred embodiment, the tail nozzle component supports changing the tail nozzle shape according to different research objectives.

[0023] According to a preferred embodiment, an ejector is provided between the air intake outlet of the fuselage main body and the nozzle inlet; the ejector is provided with a plurality of adjustable jet ports, which can simulate different flow coefficients by changing the jet port area and number parameters.

[0024] According to a preferred embodiment, the general research model for complex flow with wide Reynolds number in the internal and external flow coupling of the flying wing configuration aircraft is made of 18Ni200D steel.

[0025] The aforementioned main solution and its various further alternative solutions can be freely combined to form multiple solutions, all of which are solutions that can be adopted and are claimed in this application. Those skilled in the art, after understanding the solution of this application, will realize that there are many combinations based on the prior art and common general knowledge, all of which are technical solutions to be protected in this application, and will not be exhaustively listed here.

[0026] The beneficial effects of this application are:

[0027] This application presents a general research model for complex Reynolds number flows across a wide range of internal and external current coupling in flying-wing aircraft. It demonstrates significant innovation and practicality in modular design, generalization, oblique support, and adaptability to extreme environments. Through these design and material selections, the model not only meets research needs under different experimental conditions but also provides crucial technical support for subsequent aircraft optimization design.

[0028] Compared to existing flying-wing standard models, the universal research model for complex high Reynolds number flows involving internal and external flows in flying-wing aircraft described in this invention possesses several unique functions. First, through modular design and reserved optimization interfaces, the model can more flexibly adapt to different experimental needs, significantly improving research efficiency. Second, its sloping underbody support design is not only suitable for flattened layouts but also effectively enables the study of Reynolds number effects involving internal and external flows, providing high-precision experimental support for complex flow characteristics. Furthermore, the model utilizes 18Ni (200D) low-temperature high-strength steel, greatly expanding its applicable environmental range and meeting research needs under extreme temperature conditions. These functions make this invention more versatile and practical in the field of flying-wing aircraft research. Compared to traditional standard models, it not only overcomes technical limitations but also provides important reference value for subsequent optimization design and engineering applications. Attached Figure Description

[0029] Figure 1 This is a schematic diagram of the structure of each module of the general research model of this application;

[0030] Figure 2 This is a schematic diagram of the ventilation lip component and the plug cone component of the general research model of this application;

[0031] Figure 3 This is a structural diagram of the ejector for the general research model in this application;

[0032] Figure 4 This is a schematic diagram of the support rods and model installation for the general research model in this application;

[0033] Among them, 1-nose assembly, 2-intake lip assembly, 3-fuse upper cover plate, 4-fuse lower cover plate, 5-leading edge flap assembly, 6-tail nozzle assembly, 7-fuselage main body, 8-ventilation lip assembly, 9-plug cone assembly, 10-ejector, 11-intake duct outlet, 12-intake duct inlet, 13-nozzle inlet, 14-support rod, 15-support rod installation position on fuselage belly. Detailed Implementation

[0034] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. This application can also be implemented or applied through other different specific embodiments, and various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, unless otherwise specified, the following embodiments and features in the embodiments can be combined with each other.

[0035] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0036] In the description of this application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product of this application is in use. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on this application. In addition, the terms "first," "second," and "third," etc., are only used to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0037] Furthermore, terms such as "horizontal," "vertical," and "sag" do not imply that components must be absolutely horizontal or suspended, but rather that they can be slightly tilted. For example, "horizontal" simply means that its direction is more horizontal relative to "vertical," and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0038] In the description of this application, it should also be noted that, unless otherwise expressly specified and limited, the terms "set up," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0039] Furthermore, it should be noted that unless otherwise specified in this application, the specific structures, connections, positions, power sources, etc. involved are all things that a person skilled in the art can know without creative effort based on the prior art.

[0040] Example

[0041] refer to Figures 1 to 4As shown, this application discloses a general research model for complex Reynolds number flows across a wide range of internal and external flow coupling in a flying wing aircraft. This model is made of 18Ni200D steel. A special low-temperature high-strength steel is selected as the manufacturing material. This material exhibits excellent low-temperature performance, maintaining good toughness and strength within a temperature range of -163°C to 50°C, while also possessing corrosion resistance and fatigue resistance, making it suitable for complex wind tunnel testing environments. Specifically, in low-temperature environments, this material maintains good toughness and strength, avoiding brittle fracture caused by excessively low temperatures; while under high-load conditions, it can withstand higher stresses. Furthermore, this material also possesses good corrosion resistance and fatigue resistance, enabling it to operate stably for extended periods in complex wind tunnel testing environments.

[0042] Preferably, the general research model for complex Reynolds number flows with internal and external flow coupling of the flying wing configuration aircraft adopts a modular design concept, dividing the aircraft model into seven independent functional modules, including: nose component 1, air intake lip component 2, upper fuselage cover 3, lower fuselage cover 4, leading edge flap component 5, tail nozzle component 6, and main fuselage 7. The modules are connected through standardized interfaces, facilitating disassembly, assembly, and replacement.

[0043] Preferably, the fuselage body 7 integrates the mounting interfaces for the head assembly 1, the air intake lip assembly 2, the upper fuselage cover 3, the lower fuselage cover 4, the leading edge flap assembly 5, and the tail nozzle assembly 6. The fuselage body 7 is also designed with an internal flow channel, a measuring balance mounting interface, and reserved sensor mounting positions.

[0044] In the specific design, the nose section 1 and the main fuselage 7 adopt an independent modular design, which not only facilitates the compact layout of the force balance but also effectively reduces the error of the force measurement test. The air intake lip section 2 is designed independently, allowing for flexible configuration of different shapes of the air intake lip section 8 and the plug cone section 9. At the same time, the design of the upper and lower fuselage covers fully considers experimental requirements, providing convenient conditions for the arrangement of internal pressure measuring hoses, pulsating pressure sensors, acceleration sensors, and angle of attack sensors. In addition, the replaceable leading edge flap section 5 can quickly adjust the deflection angle of the leading edge flap according to different experimental requirements, significantly improving the model's adaptability to various flow characteristics. The tail nozzle section 6 also adopts an independent design, supporting the replacement of different tail nozzle shapes according to different research objectives, thereby achieving more flexible design optimization.

[0045] By employing a modular design approach, this application not only achieves flexible connections and interchangeability between components but also significantly improves experimental efficiency and system maintainability. This innovative design concept, while meeting the needs of researching complex flow characteristics, significantly reduces maintenance costs and time losses caused by the failure of a single component.

[0046] Preferably, the general research model for complex Reynolds number flows across a wide range of internal and external flow coupling in flying wing aircraft further includes a sloping support structure. This sloping support structure includes a strut 14 for connecting and fixing the research model. The strut 14 is a V-structure design, designed to adapt to the flattened layout of the flying wing aircraft while retaining the tail nozzle function and effectively reducing the impact of the tail support on the wake flow structure. One end of the strut 14 is connected to a measuring balance via an internal conical hole, and the other end is connected to a cavity mechanism via a cylindrical surface and tightened with screws.

[0047] Specifically, interfaces for conformal connection with the sloping underbody support are located in areas with greater thickness in the main fuselage (7). Regarding the strut design, a "V"-shaped optimized structure is adopted to address potential interference areas at the tail of the fuselage, minimizing interference with the internal flow channels and tail nozzle profile, thereby ensuring the stability of aerodynamic (moment) characteristics, especially the internal flow characteristics. Furthermore, the "V"-shaped strut design significantly reduces the impact of the tail support on the wake field, maintaining the excellent aerodynamic performance of the flying wing configuration and providing a reliable experimental basis for studying the coupling effect between internal and external flows. This innovative design, while meeting the requirements of a flattened layout, ensures the stability of the aircraft's aerodynamic characteristics and the high practicality of the research model.

[0048] Preferably, the nose section 1 includes the head shape structure of a flying wing aircraft, and an acceleration sensor mounting interface is integrated inside the nose section 1. The nose section 1 is manufactured using CNC machining according to the geometric parameters of the flying wing layout, and has an adapter interface for connection with the fuselage body 7. The nose section 1 and the fuselage body 7 are fitted with a shaft hole, positioned by a pin, and tightened by screws.

[0049] Preferably, the inlet lip component 2 is a modular design, supporting either a plugging cone configuration or a venting configuration, with the inlet lip type selected according to experimental requirements. Specifically: Plugging cone configuration: A plugging cone component 9 is installed at the inlet 12 to isolate the internal flow, facilitating independent study of the external flow field characteristics; Ventilation configuration: A venting lip component 8 is used to allow the internal and external flow fields to interact, simulating the coupling effect of a real aircraft.

[0050] Preferably, the upper cover plate 3 and the lower cover plate 4 are detachable modules, and the upper cover plate 3 and the lower cover plate 4 have reserved sensor mounting slots inside to complete the arrangement and installation of pressure measuring hoses and pulsating pressure sensor equipment in the experiment.

[0051] Preferably, the leading edge flap component 5 supports the configuration of flaps with different deflection angles; the leading edge flap component 5 is processed according to the leading edge geometric parameters of the flying wing layout and is designed with an adapter interface to achieve rapid switching of different deflection angles.

[0052] Preferably, the tail nozzle component 6 supports changing the tail nozzle shape according to different research objectives. The shape parameters (such as convergence angle, length, etc.) of the tail nozzle component 6 are selected and processed according to experimental requirements. This ensures the compatibility of the tail nozzle with the fuselage body and enables rapid replacement through standardized interfaces.

[0053] Preferably, an ejector 10 is provided between the air intake outlet 11 of the fuselage body 7 and the nozzle inlet; the ejector 10 is provided with a plurality of adjustable jet ports, which can simulate different flow coefficients by changing the jet port area and number parameters.

[0054] This application also features a high degree of versatility in its design, meeting the experimental requirements for studying the independent external flow characteristics of low-aspect-ratio flying wing aircraft and different flow coefficients in the inlet under coupled internal and external flow conditions. Specifically, the model achieves adaptability under various operating conditions through a flexible design scheme.

[0055] Firstly, the inlet lip component 2 adopts a modular structure, allowing for selective configuration of either the plug cone component 9 or the ventilation lip component 8 based on actual needs. Using the plug cone component 9 effectively isolates the internal flow of the inlet, facilitating independent study of the influence of external flow field characteristics. Conversely, using the ventilation lip component 8 allows for simultaneous consideration of the interaction between the external and internal flow fields under the coupling effect of internal and external flows. Interfaces are reserved in the inner flow channel and tail section, enabling the installation of inlet orifice plates with different flow rates and internal flow channel suction devices within the model's inner flow channel. By replacing the inlet orifice plate or adjusting the jet parameters of the ejector 10, different flow coefficient conditions can be simulated.

[0056] The aforementioned generalized design fully demonstrates the significant advantages of this invention in terms of adaptability. The model's structure and parameter configuration can be flexibly adjusted according to actual needs, thereby meeting the research requirements under various experimental conditions. This design concept not only enhances the practicality and scalability of the technical solution but also provides important reference value for subsequent optimization design and engineering applications.

[0057] The above description is merely a preferred embodiment of this application and is not intended to limit this application. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A general research model for complex Reynolds number flows across a wide domain involving internal and external flow coupling in a flying wing aircraft, characterized in that... The general research model for complex wide-domain Reynolds number flows involving internal and external current coupling in flying wing configuration aircraft includes: The nose section (1), the air intake lip section (2), the upper fuselage cover (3), the lower fuselage cover (4), the leading edge flap section (5), the tail nozzle section (6), and the main fuselage section (7). The fuselage body (7) integrates the mounting interfaces of the head assembly (1), the air intake lip assembly (2), the upper cover plate (3), the lower cover plate (4), the leading edge flap assembly (5), and the tail nozzle assembly (6). The fuselage body (7) is designed with an internal flow channel, a measuring balance mounting interface, and a reserved sensor mounting position. The general research model for complex wide-domain Reynolds number flows involving internal and external flow coupling in flying wing configuration aircraft also includes a sloping support structure. The oblique support structure includes a support rod (14) for connecting and fixing the model of this study. The support rod (14) is a V-structure design and has an interface adapted to the support rod (14) on the fuselage body (7). One end of the support rod (14) is connected to the measuring balance through an inner conical hole, and the other end is connected to the cavity mechanism through a cylindrical surface and tightened by screws; The intake lip component (2) is a modular design that supports either a plug cone configuration or a ventilation configuration. The intake lip type can be selected according to the test requirements. Blocking cone configuration: A blocking cone component (9) is installed at the inlet (12) of the air intake to isolate the internal flow so as to facilitate independent study of the external flow field characteristics; Ventilation configuration: The ventilation lip component (8) is designed to allow the internal and external flow fields to interact, simulating the coupling effect of a real aircraft; The leading edge flap component (5) supports the configuration of flaps with different deflection angles; the leading edge flap component (5) is processed according to the leading edge geometric parameters of the flying wing layout and is designed with an adapter interface to achieve rapid switching of different deflection angles; The tail nozzle component (6) supports changing the tail nozzle shape according to different research objectives; An ejector (10) is provided between the air intake outlet (11) and the nozzle inlet (13) of the fuselage body (7). The ejector (10) is provided with several adjustable jet ports, which can simulate different flow coefficients by changing the jet port area and number parameters.

2. The flying wing layout aircraft inner-outer flow coupling wide range Reynolds number complex flow general research model according to claim 1, characterized in that, The nose section (1) includes the head shape structure of a flying wing aircraft, and the nose section (1) integrates an acceleration sensor mounting interface. The nose section (1) is manufactured using CNC machining according to the geometric parameters of the flying wing layout, and is provided with an adapter interface for connection with the fuselage body (7).

3. The flying wing layout aircraft inner-outer flow coupling wide range Reynolds number complex flow general research model according to claim 2, characterized in that, The head component (1) and the body body (7) are fitted with a shaft hole, with pin positioning and screw tightening.

4. The flying wing layout aircraft inner-outer flow coupling wide range Reynolds number complex flow general research model according to claim 1, characterized in that, The upper cover plate (3) and the lower cover plate (4) of the fuselage are detachable modules, and the upper cover plate (3) and the lower cover plate (4) of the fuselage have reserved sensor installation slots inside to complete the arrangement and installation of pressure measuring hoses and pulsating pressure sensor equipment in the experiment.

5. The flying wing layout aircraft inner-outer flow coupling wide range Reynolds number complex flow general research model according to claim 1, characterized in that, The general research model for complex Reynolds number flow in a wide range of internal and external flow coupling of flying wing configuration aircraft is made of 18Ni200D steel.

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