A support device and test system for virtual flight tests in a low-speed wind tunnel

Abstract

The present application provides a support device and a test system for virtual flight tests in a low-speed wind tunnel, which relate to the technical field of wind tunnel tests. The support device for virtual flight tests in a low-speed wind tunnel includes N-level moving modules, satisfying: N is a positive integer and N≥2; wherein, the (N-1)-th level moving module is connected to the N-th level moving module, the N-th level moving module is used to drive the (N-1)-th level moving module to move along a preset direction, and the first level moving module is connected to the aircraft model, the first level moving module is used to drive the aircraft model to move along a preset direction, and the preset direction can enable the aircraft model to switch between multiple pitch attitudes. The present application can not only take into account a relatively small wind tunnel space, but also ensure the structural strength, and reduce the windward area, so that a very small blockage ratio can be achieved, ensuring the reliability and accuracy of the test.

Description

Technical Field

[0001] The present application relates to the technical field of wind tunnel tests, and particularly to a support device and a test system for low-speed wind tunnel virtual flight tests. Background Art

[0002] The low-speed wind tunnel virtual flight test technology is a dynamic test simulation technology for realizing the flight verification of a dynamically similar scaled model based on a test device, and is used for carrying out aerodynamic verification and evaluation, flight state evaluation, stall simulation, and post-stall maneuver simulation in the early stage of aircraft development in a low-speed wind tunnel.

[0003] As the basic facility for virtual flight tests, the dynamic adjustment ability of the test model of the low-speed wind tunnel virtual flight test device is very important. Usually, the support device for the low-speed wind tunnel virtual flight test adopts a Hooke hinge structure or a ball hinge structure to realize the combined rotation of the model. However, it is impossible to simulate the aerodynamic characteristics and flight state evaluation of the model at a large pitch angle. Summary of the Invention

[0004] In view of this, the purpose of the present application is to overcome the deficiencies in the prior art, and provide a support device for low-speed wind tunnel virtual flight tests and a low-speed wind tunnel virtual flight test system, which can not only take into account a relatively small wind tunnel space, but also ensure the structural strength, reduce the windward area, achieve a very small blockage ratio, and ensure the reliability and accuracy of the test.

[0005] The present application provides the following technical solutions:

[0006] In a first aspect, an embodiment of the present application provides a support device for low-speed wind tunnel virtual flight tests, and the support device for low-speed wind tunnel virtual flight tests includes:

[0007] N-level moving modules, where N is a positive integer and N≥2; wherein, the (N - 1)-th level moving module is connected to the N-th level moving module, the N-th level moving module is used to drive the (N - 1)-th level moving module to move along a preset direction, and the first level moving module is connected to the aircraft model, and the first level moving module is used to drive the aircraft model to move along the preset direction, and the preset direction can enable the aircraft model to switch between multiple pitch attitudes.

[0008] In some embodiments of the first aspect, the preset direction has a descending section and an ascending section arranged in sequence, and the preset direction is located in a vertical plane.

[0009] In some embodiments of the first aspect, the preset direction is set as an arc.

[0010] In some embodiments of the first aspect, the moving module includes:

[0011] A guide rail that extends along the preset direction;

[0012] A slider that is slidably connected to the guide rail;

[0013] A rack that is disposed on the guide rail and extends along the preset direction;

[0014] A gear that meshes with the rack;

[0015] A driving part that is connected to the gear and is used to drive the gear to rotate;

[0016] Wherein, the driving part of the (N - 1)-th stage of the moving module is connected to the guide rail of the N-th stage of the moving module.

[0017] In some embodiments of the first aspect, the driving part of the (N - 1)-th stage of the moving module is connected to one end of the guide rail of the N-th stage of the moving module downstream in the wind direction.

[0018] In some embodiments of the first aspect, the driving part includes a motor and a speed reducer. The rotating shaft of the motor is connected to the power input shaft of the speed reducer, and the power output shaft of the speed reducer is connected to the gear.

[0019] In some embodiments of the first aspect, the driving part is connected to the slider.

[0020] In some embodiments of the first aspect, the low-speed wind tunnel virtual flight test support device further includes a support rod. The support rod has a first section and a second section that are connected in sequence. The first section is connected to the aircraft model and extends along a direction parallel to the longitudinal axis of the aircraft model, and the second section is perpendicular to the first section.

[0021] In some embodiments of the first aspect, the first section is connected to the tail end of the aircraft model and extends along the longitudinal axis.

[0022] In a second aspect, the present application further provides a low-speed wind tunnel virtual flight test system, which includes the low-speed wind tunnel virtual flight test support device according to any one of the above embodiments.

[0023] The embodiments of the present application have the following advantages:

[0024] The present application provides a support device for virtual flight tests in a low-speed wind tunnel. The Nth-level moving module is connected to the (N - 1)th-level moving module, and the Nth-level moving module can drive the (N - 1)th-level moving module to move in a predetermined direction. Such a design makes the entire system more flexible and can achieve complex motion patterns. The first-level moving module is directly connected to the aircraft model and is responsible for driving the model to move in a preset direction. It should be noted that each moving module can move independently. That is to say, the movement of each moving module can drive the aircraft model to move in the preset direction, thereby achieving a large range of adjustment of the pitch angle of the aircraft model. Moreover, the selection of the preset direction enables the aircraft model to switch between different pitch attitudes, which is crucial for evaluating the performance under different flight states. Obviously, the new design of the support device takes into account the space limitations inside the wind tunnel and can adapt to a smaller wind tunnel space. Secondly, the strength of the structure is ensured, enabling the device to remain stable under high-stress conditions. Also, the windward area of the device is reduced, the interference to the airflow is decreased, and the accuracy of the test data is improved. Furthermore, due to the optimization in design, the blockage degree of the device is reduced, ensuring that the test environment is closer to real flight conditions. This improved support device represents an important technological advancement for virtual flight tests in low-speed wind tunnels and helps to more accurately evaluate the performance of aircraft under various flight conditions.

[0025] The present application also relates to a virtual flight test system for a low-speed wind tunnel. Since the above-mentioned support device for virtual flight tests in a low-speed wind tunnel has the above technical effects, the virtual flight test system for a low-speed wind tunnel including this support device should have the same technical effects, which will not be elaborated here.

[0026] To make the above objects, features, and advantages of the present invention more obvious and understandable, the following specific preferred embodiments are given, and in conjunction with the accompanying drawings, the detailed description is as follows. Description of the Drawings

[0027] To more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present application and should not be regarded as limiting the scope. For those of ordinary skill in the art, without creative efforts, other related drawings can also be obtained based on these drawings.

[0028] Figure 1 Shows a schematic structural diagram of a support device for virtual flight tests in a low-speed wind tunnel provided by an embodiment of the present application in a horizontal state;

[0029] Figure 2 Shows a schematic structural diagram of a support device for virtual flight tests in a low-speed wind tunnel provided by an embodiment of the present application in a nose-up state;

[0030] Figure 3 The figure shows a schematic structural diagram of a low-speed wind tunnel virtual flight test support device provided by an embodiment of the present application in a prone position state.

[0031] Main element symbol description:

[0032] 100 - Moving module; 110 - Guide rail; 120 - Rack; 130 - Slide block; 140 - Reducer; 150 - Motor; 200 - Support rod; 210 - First section; 220 - Second section; 300 - Aircraft model. Detailed implementation manners

[0033] The embodiments of the present application will be described in detail below. Examples of the embodiments are shown in the accompanying drawings, where the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary only for explaining the present application and should not be construed as limiting the present application.

[0034] It should be noted that when an element is referred to as being "fixed to" another element, it can be directly on the other element or there may also be an intermediate element. When an element is considered to be "connected" to another element, it can be directly connected to the other element or there may be an intermediate element at the same time. On the contrary, when an element is referred to as being "directly on" another element, there is no intermediate element. The terms "vertical", "horizontal", "left", "right" and similar expressions used herein are for illustrative purposes only.

[0035] In the present application, unless otherwise clearly defined and limited, the terms "installed", "connected", "connected to", "fixed" and other terms should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements or the interaction relationship between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances.

[0036] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present application, the meaning of "a plurality" is two or more unless otherwise clearly and specifically defined.

[0037] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the technical field to which this application belongs. The terms used in the description of the template herein are for the purpose of describing specific embodiments only and are not intended to limit this application. The term "and / or" used herein includes any and all combinations of one or more of the related listed items.

[0038] In the related art, the low-speed wind tunnel virtual flight test technology is a dynamic test simulation technology based on a test device to achieve dynamic similarity scaled model flight verification, and is used for aerodynamic verification and evaluation, flight state evaluation, stall simulation, and post-stall maneuver simulation in the early stage of aircraft development in a low-speed wind tunnel.

[0039] As the basic facility of the virtual flight test, the dynamic adjustment ability of the test model of the low-speed wind tunnel virtual flight test device is very important. Usually, the support device of the low-speed wind tunnel virtual flight test adopts a Hooke hinge structure or a ball hinge structure to achieve the combined rotation of the model. However, it is impossible to simulate the aerodynamic characteristics and flight state evaluation of the model at a large pitch angle. Moreover, the test device is large in volume and requires a large pit to adapt to the test environment, increasing the construction cost and requiring more stringent test conditions.

[0040] As shown in FIG. 1, Figure 2 and Figure 3 shown, to solve the above technical problems, the embodiments of the present application provide a support device for a low-speed wind tunnel virtual flight test. The support device for the low-speed wind tunnel virtual flight test includes an N-stage moving module 100, satisfying: N is a positive integer and N≥2; wherein, the (N - 1)-th stage moving module 100 is connected to the N-th stage moving module 100, the N-th stage moving module 100 is used to drive the (N - 1)-th stage moving module 100 to move along a preset direction, and the first stage moving module 100 is connected to the aircraft model 300, and the first stage moving module 100 is used to drive the aircraft model 300 to move along a preset direction, and the preset direction can enable the aircraft model 300 to switch between multiple pitch attitudes.

[0041] In these embodiments, the support device for the low-speed wind tunnel virtual flight test is composed of an N-stage moving module 100, where N is a positive integer greater than or equal to 2. This means that at least two moving modules 100 work together. Exemplarily, in this embodiment, the number of moving modules 100 is taken as 2. Of course, in other embodiments, the number of moving modules 100 can also be 3, 4, 5, 6, 7, 8, etc., which are not specifically limited herein.

[0042] Among them, the Nth - level moving module 100 is connected to the (N - 1)th - level moving module 100, and the Nth - level moving module 100 can drive the (N - 1)th - level moving module 100 to move in a predetermined direction. Such a design makes the whole system more flexible and can achieve complex motion patterns. The first - level moving module 100 is directly connected to the aircraft model 300 and is responsible for driving the model to move in a preset direction. It should be noted that each moving module 100 can move independently. That is to say, the movement of each moving module 100 can drive the aircraft model 300 to move in the preset direction, thereby achieving a large - range adjustment of the pitch angle of the aircraft model 300.

[0043] The selection of the preset direction enables the aircraft model 300 to switch between different pitch attitudes, which is crucial for evaluating the performance under different flight states. Obviously, the new design of the support device takes into account the space limitations inside the wind tunnel and can adapt to a smaller wind tunnel space. Secondly, the strength of the structure is ensured, enabling the device to remain stable under high - stress conditions. Also, the windward area of the device is reduced, reducing the interference with the airflow and improving the accuracy of the test data. Moreover, due to the optimization of the design, the blockage degree of the device is reduced, ensuring that the test environment is closer to the real flight conditions. This improved support device is an important technological advancement for virtual flight tests in low - speed wind tunnels and helps to more accurately evaluate the performance of aircraft under various flight conditions.

[0044] Therefore, the support device for virtual flight tests in low - speed wind tunnels provided in this application adopts a structure of multiple - level moving modules 100. Each moving module 100 can move relatively independently and can drive the adjacent moving module 100 to move in a preset direction. This method allows the aircraft model 300 to switch between multiple pitch attitudes, that is, it can achieve a large - range adjustment of the pitch angle of the aircraft model 300, thereby better simulating the actual flight conditions.

[0045] In some embodiments, the preset direction has a descending section and an ascending section arranged in sequence, and the preset direction is located in a vertical plane.

[0046] In these embodiments, such a design enables the support device for virtual flight tests in low - speed wind tunnels to better simulate the dynamic behavior of an aircraft under complex flight states. Among them, the definition of the preset direction:

[0047] Descending section: The flight model first descends along a certain path in the vertical plane.

[0048] Ascending section: Then, the flight model ascends along another path in the vertical plane. Among them, the entire preset direction (i.e., the movement trajectory of the flight model) is located in a plane perpendicular to the ground.

[0049] Obviously, through this design of the preset direction, complex dynamic adjustments of the flight model in the vertical plane can be achieved, and the dynamic adjustments include changes in the pitch angle. This path design enables the flight model to switch between multiple pitch postures, thereby better simulating the dynamic behavior of the aircraft during actual flight.

[0050] Obviously, by setting the descent section and the ascent section, the dynamic characteristics of the aircraft in various flight states such as takeoff, climb, dive, and zoom can be more realistically simulated. It helps to evaluate the performance of the aircraft under extreme flight conditions, such as stall recovery and post-stall maneuvers. Moreover, by adjusting the specific parameters (such as angle, length, etc.) of the descent section and the ascent section, different flight states can be simulated, enhancing the flexibility of the test device. This design enables the test device to adapt to the different requirements of various aircraft models.

[0051] In addition, by optimizing the path design, the windward area can be further reduced, the interference to the airflow in the wind tunnel can be decreased, and the reliability and accuracy of the test can be improved. At the same time, this design helps to maintain the strength of the structure and ensure the stability of the device during complex movements.

[0052] Exemplarily, the specific paths of the descent section and the ascent section can be pre-planned through computer simulation software to ensure that the paths meet the test requirements. According to the test objectives, parameters such as the curvature, length, and angle of the paths are adjusted. A high-precision control system is used to drive the flight model to move along the preset path, ensuring that the movement in each stage can be precisely executed. The control system needs to be able to adjust the attitude of the model in real time to adapt to the changes in the path. During the test, high-precision sensors are used to monitor the attitude and position of the flight model in real time to ensure the accurate execution of the path. Through the feedback mechanism, the position and attitude of the model are adjusted in a timely manner to cope with any minor deviations.

[0053] In some embodiments, the preset direction is set to be arc-shaped.

[0054] In these embodiments, the preset direction is set to be arc-shaped, which means that the movement path of the flight model is not a simple straight line or a segmented straight line, but along an arc path. It can better simulate the complex dynamic behavior experienced by the aircraft during actual flight, especially when making pitch attitude changes.

[0055] The preset direction is designed as an arc path, which means that the flight model will move along an arc or curve with a determined radius of curvature. Each stage in the N-stage moving module 100 can work independently or cooperatively to drive the flight model to move along the arc path. The first-stage moving module 100 is directly connected to the flight model and is responsible for driving the model to move along the arc path.

[0056] The arc path can more accurately simulate the aerodynamic characteristics of the aircraft at different pitch attitudes, thereby improving the accuracy and reliability of the test data. It reduces the unnatural transitions that may occur with a straight-line path, making the test closer to actual flight conditions. By adjusting the specific parameters of the arc path (such as radius, starting point, and ending point, etc.), different flight states can be simulated, enhancing the flexibility of the test device.

[0057] In some embodiments, the moving module 100 includes a guide rail 110, a slider 130, a rack 120, a gear, and a driving part. The guide rail 110 extends along the preset direction; the slider 130 is slidably connected to the guide rail 110; the rack 120 is disposed on the guide rail 110 and extends along the preset direction; the gear meshes with the rack 120; the driving part is connected to the gear and is used to drive the gear to rotate; wherein, the driving part of the (N - 1)th - level moving module 100 is connected to the guide rail 110 of the Nth - level moving module 100.

[0058] In these embodiments, the moving module 100 includes a guide rail 110, a slider 130, a rack 120, a gear, and a driving part. This design enables the virtual flight test support device of the low - speed wind tunnel to achieve precise dynamic adjustment and perform complex movements in the vertical plane or any preset direction.

[0059] The guide rail 110 extends along the preset direction, providing a guiding function for the slider 130 to ensure that the slider 130 moves along the specified path. The slider 130 is slidably connected to the guide rail 110 and can slide freely on the guide rail 110, driving the flight model to move along the preset direction. That is to say, the slider 130 remains stationary while the guide rail 110 moves in the preset direction to support and limit the guide rail 110. The rack 120 is disposed on the guide rail 110 and extends along the preset direction, meshing with the gear and used to convert the rotational motion of the gear into the linear motion of the slider 130. The gear meshes with the rack 120, and the rotation of the gear drives the slider 130 on the rack 120 to move along the guide rail 110. The driving part is connected to the gear and is used to drive the gear to rotate, thereby driving the guide rail 110 to move along the preset direction.

[0060] Among them, this cascading structure enables each level of the moving module 100 to drive each other, forming a multi - level linkage system. The driving part of the (N - 1)th - level moving module 100 drives the gear to rotate, driving the guide rail 110 on the rack 120 to move along the preset direction, and then driving the guide rail 110 of the Nth - level moving module 100 to move.

[0061] Obviously, through the meshing transmission of the gear and the rack 120, very precise displacement control can be achieved, ensuring that the flight model can move precisely along the preset path. The design of the guide rail 110 and the slider 130 ensures the stability of the moving module 100, and good positioning accuracy can be maintained even during high-speed movement. The cascaded structure of the multi-stage moving module 100 enables the entire system to achieve complex motion trajectories and simulate the dynamic behavior of the aircraft in different flight states. By adjusting the parameters of the driving parts at different levels, different levels of motion control can be achieved, making the test device more flexible and diverse. The transmission mode of the gear and the rack 120 has high reliability and reduces errors caused by the breakage or failure of the transmission chain.

[0062] Exemplarily, a set of support devices for virtual flight tests in a low-speed wind tunnel is provided, which includes two-stage moving modules 100. The guide rail 110 of the first-stage moving module 100 is arranged along a preset direction, and the slider 130 is slidably connected to the guide rail 110. The rack 120 is fixed on the guide rail 110, and the gear meshes with the rack 120. The driving part is connected to the gear and drives the gear to rotate, driving the slider 130 to move up and down along the guide rail 110.

[0063] The movement of the guide rail 110 of the first-stage moving module 100 will drive the guide rail 110 and the slider 130 of the second-stage moving module 100. The second-stage moving module 100 also includes a guide rail 110, a slider 130, a rack 120, a gear, and a driving part to achieve movement along a preset direction. Through this design, complex movements of the flight model in the preset direction in the vertical plane can be achieved, thus better simulating the dynamic behavior of the aircraft during actual flight.

[0064] In some embodiments, the driving part of the (N - 1)-th stage moving module 100 and the guide rail 110 of the N-th stage moving module 100 are connected at one end downstream in the wind direction.

[0065] In these embodiments, this design takes into account the direction of the airflow in the wind tunnel, aiming to reduce airflow interference and improve the reliability and accuracy of the test. The wind direction refers to the direction of the airflow in the wind tunnel, usually flowing from one end face of the wind tunnel to the other end face.

[0066] Among them, the driving part of the (N - 1)-th stage moving module 100 is connected to the guide rail 110 of the N-th stage moving module 100 at the downstream end in the wind direction, which means the driving part is located at the tail end of the guide rail 110 instead of the windward end. Placing the driving part at the downstream end of the guide rail 110 can reduce the interference of the driving part on the air flow. The driving part is usually large and has a complex structure. Placing it at the windward end will increase the obstruction to the air flow, resulting in air flow disorder and affecting the accuracy of test data. Secondly, by reducing the influence of the driving part on the air flow, the air flow can be ensured to be more stable, thereby improving the reliability and accuracy of test data. Moreover, placing the driving part at the downstream end can reduce the direct mechanical interference of the driving part on the guide rail 110 and improve the stability of the whole system. Also, the downstream connection design can simplify the layout of the guide rail 110, make the guide rail 110 smoother, and reduce unnecessary mechanical interference.

[0067] In some embodiments, the driving part includes a motor 150 and a speed reducer 140. The rotating shaft of the motor 150 is connected to the power input shaft of the speed reducer 140, and the power output shaft of the speed reducer 140 is connected to a gear.

[0068] In these embodiments, this design enables the drive system to provide precise control and sufficient torque while reducing the rotational speed to meet the requirements of the virtual flight test support device in a low-speed wind tunnel. The motor 150 is the core power source of the drive system, providing the initial power output. When selecting the motor 150, factors such as power, torque, and rotational speed should be considered to ensure that the power requirements for driving the gear can be met.

[0069] The speed reducer 140 is used to reduce the rotational speed of the motor 150 and increase the torque, so that the gear can drive the rack 120 smoothly. The speed reducer 140 usually includes multiple stages of gear sets, and the effect of speed reduction and torque increase is achieved through the meshing of gears. The rotating shaft of the motor 150 is directly connected to the power input shaft of the speed reducer 140, and the mechanical connection is realized through a coupling or other connection methods. The power output shaft of the speed reducer 140 is connected to a gear, and the rack 120 is driven through the gear to realize the movement of the guide rail 110 in the preset direction.

[0070] When the motor 150 starts, the rotating shaft of the motor 150 begins to rotate, transmitting power to the power input shaft of the speed reducer 140. The speed reducer 140 reduces the rotational speed and increases the torque through the action of the internal gear set, converting the high-speed low-torque of the motor 150 into low-speed high-torque. The power output shaft of the speed reducer 140 drives the gear to rotate, and the gear meshes with the rack 120, thereby driving the rack 120 to drive the guide rail 110 to move in the preset direction.

[0071] Obviously, the combination of the motor 150 and the speed reducer 140 can provide precise speed and position control, ensuring that the flight model can move precisely along the preset path. The use of the speed reducer 140 can achieve finer speed adjustment and improve the control accuracy of the entire system. The speed reducer 140 can significantly increase the output torque, enabling the drive system to provide sufficient driving force at low speeds and ensuring that the slider 130 and the flight model can move smoothly.

[0072] Exemplarily, the motor 150 is a servo motor 150 to provide precise position control. Of course, in other embodiments, the motor 150 can also be a stepper motor 150, a DC motor 150, an AC motor 150, etc.

[0073] In some embodiments, the driving part is connected to the slider 130.

[0074] In these embodiments, that is to say, the housing of the motor 150 is fixed to the slider 130, simplifying the overall structure, making the overall structure more compact, and reducing the influence on the air flow in the wind tunnel.

[0075] In some embodiments, the low-speed wind tunnel virtual flight test support device further includes a support rod 200. The support rod 200 has a first section 210 and a second section 220 connected in sequence. The first section 210 is connected to the aircraft model 300, and the first section 210 extends along a direction parallel to the longitudinal axis of the aircraft model 300. The second section 220 is perpendicular to the first section 210.

[0076] In these embodiments, the first section 210 is connected to the aircraft model 300 and extends along a direction parallel to the longitudinal axis of the aircraft model 300. The main function of this section is to fix the aircraft model 300 at an appropriate position in the wind tunnel and ensure the longitudinal stability of the model. The second section 220 is perpendicular to the first section 210 and is usually connected to the slider 130 of the first-stage moving module 100. The main function of this section is to provide vertical support and ensure the vertical stability of the model in the wind tunnel.

[0077] Exemplarily, the first section 210 is connected to the aircraft model 300 through fasteners (such as bolts, pins, etc.) to ensure the fixation of the model in the wind tunnel.

[0078] The second section 220 is connected to the first-stage moving module 100 or other support structures through appropriate connection methods (such as welding, threaded connection, etc.).

[0079] Obviously, by driving the moving module 100, the support rod 200 and the aircraft model 300 can be moved in a preset direction to achieve dynamic adjustment of the model. Moreover, through the combination of the first section 210 and the second section 220, better all-round support can be provided to ensure the stability and accuracy of the aircraft model 300 in the wind tunnel. The design of the support rod 200 can reduce the influence of the airflow on the model and improve the accuracy and reliability of the test data.

[0080] In some embodiments, the first section 210 is connected to the tail end of the aircraft model 300, and the first section 210 is arranged to extend along the longitudinal axis.

[0081] Obviously, in these embodiments, by specifically defining the connection position between the first section 210 and the aircraft model 300, the air flow can be further optimized, the interference to the airflow can be reduced, and the accuracy of the test data can be improved.

[0082] Exemplarily, one end of the first section 210 is connected to the upper end of the second section 220, the other end of the first section 210 is connected to the end face of the tail end of the flight model, and the lower end of the second section 220 is connected to the slider 130 of the first-stage moving module 100.

[0083] In some embodiments, the present application further provides a low-speed wind tunnel virtual flight test system, and this low-speed wind tunnel virtual flight test system includes the low-speed wind tunnel virtual flight test support device as described in any one of the above embodiments.

[0084] Since the above-mentioned low-speed wind tunnel virtual flight test support device has the above technical effects, the low-speed wind tunnel virtual flight test system including this low-speed wind tunnel virtual flight test support device should have the same technical effects, which will not be elaborated here.

[0085] In all the examples shown and described here, any specific value should be interpreted as merely exemplary and not as a limitation. Therefore, other examples of the exemplary embodiments may have different values.

[0086] It should be noted that: similar reference numerals and letters denote similar items in the following drawings. Therefore, once an item is defined in one drawing, it does not need to be further defined and explained in subsequent drawings.

[0087] The above-described embodiments only represent several implementation manners of the present application. Their descriptions are relatively specific and detailed, but they should not be construed as limiting the scope of the present application. It should be pointed out that for those of ordinary skill in the art, without departing from the concept of the present application, several modifications and improvements can still be made, and these all belong to the protection scope of the present application.

Claims

1. A low-speed wind tunnel virtual flight test support device, characterized in that: The low-speed wind tunnel virtual flight test support device comprises: N levels of mobile modules, N is a positive integer, and N ≥ 2; wherein the mobile module of the N-1th level is connected to the mobile module of the Nth level, and the mobile module of the Nth level is used to drive the mobile module of the N-1th level to move along a preset direction, and the mobile module of the 1st level is connected to the aircraft model, and the mobile module of the 1st level is used to drive the aircraft model to move along the preset direction, and the preset direction can enable the aircraft model to switch between multiple pitch attitudes; The preset direction has a descending section and an ascending section arranged in sequence, the preset direction is located in a vertical plane, and the preset direction is arranged in an arc shape; The mobile module comprises: A guide rail, wherein the guide rail is extended along the preset direction; A slider, wherein the slider is slidably connected to the guide rail; A rack, the rack being arranged on the guide rail and extending along the preset direction; a gear, the gear meshing with the rack; A driving part, the driving part is connected to the gear, and the driving part is used to drive the gear to rotate; Wherein, the driving part of the mobile module of the N-1th level is connected to the guide rail of the mobile module of the Nth level; The driving unit of the moving module of the N-1th stage and the guide rail of the moving module of the Nth stage are connected at one end downstream in the wind direction.

2. The low-speed wind tunnel virtual flight test support device according to claim 1 is characterized in that: The driving part includes a motor and a reducer, the rotating shaft of the motor is connected to the power input shaft of the reducer, and the power output shaft of the reducer is connected to the gear.

3. The low-speed wind tunnel virtual flight test support device according to claim 2 is characterized in that: The driving part is connected to the slider.

4. The low-speed wind tunnel virtual flight test support device according to any one of claims 1 to 3, characterized in that: The low-speed wind tunnel virtual flight test support device also includes a support rod, which has a first section and a second section connected in sequence, the first section is connected to the aircraft model, and the first section extends in a direction parallel to the longitudinal axis of the aircraft model, and the second section is perpendicular to the first section.

5. The low-speed wind tunnel virtual flight test support device according to claim 4 is characterized in that: The first section is connected to the tail end of the aircraft model, and the first section is extended along the longitudinal axis.

6. A low-speed wind tunnel virtual flight test system, characterized in that: The low-speed wind tunnel virtual flight test system comprises a low-speed wind tunnel virtual flight test support device according to any one of claims 1 to 5.

Images