A testing device and testing method for flapping-wing aircraft

Abstract

This invention discloses a testing device and method for flapping-wing aircraft. The testing device includes a base, a clamping assembly, at least one mounting component, and a sensor. The base surface has a first slide rail and multiple spaced-apart second slide rails, the second slide rails being perpendicular to the first slide rail. Each second slide rail includes a sub-slide rail symmetrically arranged relative to the first slide rail, and the sub-slide rail is connected to the first slide rail. The clamping assembly is disposed on the surface of the base. The mounting component is retractably disposed on the surface of the base and can move along the first slide rail and the sub-slide rails. The sensor is installed at the end of each mounting component furthest from the base. This embodiment's technical solution, by acquiring wind field values ​​from the flapping-wing aircraft, can effectively assess whether the airflow direction and volume generated by the flapping wing are reasonable, facilitating adjustments to the structure and design by R&D personnel based on test results, reducing R&D difficulty and shortening the R&D cycle.

Description

Technical Field

[0001] This invention relates to the field of flapping-wing aircraft testing technology, and in particular to a testing device and method for flapping-wing aircraft. Background Technology

[0002] Ornithoptering aircraft possess excellent maneuverability, stability, and flexibility, enabling rapid flapping, twisting, and bending of their wings. This allows them to fully utilize unsteady aerodynamic characteristics to achieve high lift and a high lift-to-drag ratio, efficiently and with low energy consumption completing flight maneuvers such as forward flight, hovering, and sharp turns. Learning from the advantages of flying organisms and drawing inspiration from their airframe structures and flight mechanisms, the biomimetic development of highly maneuverable, low-energy-consumption ornithoptering aircraft holds broad application prospects. Because the aerodynamic principles of ornithoptering aircraft differ from those of fixed-wing or rotary-wing aircraft, unique testing equipment is required. Ornithoptering aircraft testing commonly employs field flight tests or wind tunnel tests for measurement and recording. Additionally, some testing devices for ornithoptering aircraft also exist.

[0003] However, existing testing devices are mostly developed for micro flapping-wing aircraft and are not suitable for large bird-inspired flapping-wing aircraft. Furthermore, they often employ a stationary flapping-wing test method, where the aircraft fuselage remains stationary while the wings flap (e.g., CN202010769337.4), which cannot directly reflect the actual flight performance of the flapping-wing aircraft. Some bird-inspired aircraft test benches can perform axial flapping-wing flight, but the initial test angle is with the wings perpendicular to the ground. Achieving normal flapping-wing flight requires very high lift from the flapping-wing aircraft, making them unsuitable for the trial-and-error testing phase of flapping-wing aircraft. Summary of the Invention

[0004] To address the aforementioned technical problems, this invention provides a testing device and method for flapping-wing aircraft.

[0005] In a first aspect, embodiments of this application provide a testing apparatus for a flapping-wing aircraft, comprising:

[0006] The base has a first slide rail and a plurality of spaced second slide rails on its surface, the second slide rails being perpendicular to the first slide rail; wherein each second slide rail includes a sub-slide rail symmetrically arranged relative to the first slide rail, the sub-slide rails being connected to the first slide rail;

[0007] A clamping assembly, disposed on the surface of the base, is used to clamp the flapping-wing aircraft to be tested;

[0008] At least one mounting element is telescopically disposed on the surface of the base and is movable along the first slide and the sub-slide;

[0009] A sensor, mounted at the end of each of the mounting components away from the base, is used to detect the wind speed of the flapping-wing aircraft to be tested, which is clamped on the clamping assembly.

[0010] In one embodiment, three mounting components are provided, namely a first mounting component, a second mounting component, and a third mounting component, wherein, when testing the flapping-wing aircraft with the clamping assembly, the first mounting component, the second mounting component, and the third mounting component are located on the same straight line.

[0011] In one embodiment, the mounting component includes a first mounting rod and a second mounting rod, the second mounting rod being retractably disposed within the first mounting rod, the sensor being detachably connected to the end of the second mounting rod away from the base, and the end of the first mounting rod facing the base extending into the first slide rail or the sub-slide rail.

[0012] In one embodiment, an adjusting member is further included, which is located on the outer side of the end of the first mounting rod away from the base, for adjusting the length of the second mounting rod retracted into the first mounting rod.

[0013] In one embodiment, a fastener is further included, which is sleeved on one end of the first mounting rod facing the base for locking the first mounting rod onto the base.

[0014] In one embodiment, the clamping assembly includes a fixing frame, an adjusting rod, a left clamp, and a right clamp. The fixing frame is fixed to the surface of the base, the left clamp is fixed to the fixing frame, and the right clamp is sleeved on the adjusting rod, with one end of the adjusting rod rotatably connected to the left clamp.

[0015] When the adjusting rod rotates, the right gripper is driven to move closer to or away from the left gripper.

[0016] In one embodiment, the fixing frame includes a fixing plate and multiple support rods, one end of each support rod is connected to the surface of the base, the fixing plate is installed on the other end of each support rod, the left gripper is fixedly connected to the fixing plate, and the adjusting rod is located above the fixing plate.

[0017] In one embodiment, a plurality of mounting holes are formed on the surface of the base, and a plurality of support rods extend into each of the mounting holes so that the support rods are detachably connected to the base.

[0018] In one embodiment, the sensor includes a thermal anemometer.

[0019] Secondly, embodiments of this application also provide a testing method for an flapping-wing aircraft, the method comprising the following steps:

[0020] The flapping-wing aircraft to be tested is clamped, and multiple sensors at the same height and in a straight line are placed behind the flapping-wing aircraft; one sensor is located directly behind the flapping-wing aircraft, and two sensors are located at the midpoints of the two wings of the flapping-wing aircraft respectively.

[0021] Control the flapping-wing aircraft to fly according to preset motion parameters; among which, the motion parameters include flapping frequency and flapping amplitude;

[0022] Adjust the position of the sensor to test and record the wind speed of the flapping-wing aircraft under test at different wing angles.

[0023] Compared with the prior art, the technical solutions provided in this application have the following advantages:

[0024] The flapping-wing aircraft to be tested is clamped by a clamping assembly, and then the mounting component with sensors is placed on the base. The position of the mounting component on the base is adjusted by using the first slide and sub-slide provided on the base, thereby adjusting the test position of the sensors. At the same time, the test height of the sensors can be adjusted by extending and retracting the mounting component, so as to obtain the wind field value of the flapping-wing aircraft. This allows for an effective assessment of whether the airflow direction and wind volume generated by the flapping wing are reasonable. This facilitates the R&D personnel to adjust the structure and design based on the test results, reducing the R&D difficulty and shortening the development cycle. Attached Figure Description

[0025] Figure 1 This is a top view of the test device for the flapping-wing aircraft according to an embodiment of this application;

[0026] Figure 2 This is a schematic diagram of the structure of the test device for the flapping-wing aircraft according to an embodiment of this application;

[0027] Figure 3 This is a schematic diagram of the structure of the mounting component in the test device of the flapping-wing aircraft according to an embodiment of this application;

[0028] Figure 4 This is a schematic diagram of the clamping component in the testing device for the flapping-wing aircraft according to an embodiment of this application;

[0029] Figure 5 This is a schematic diagram of the base structure in the test device of the flapping-wing aircraft according to an embodiment of this application;

[0030] Figure 6 It is a three-dimensional curve of data when the wings of an flapping-wing aircraft with a wing installation angle of 0° are aligned with the sensor.

[0031] Figure 7 It is a three-dimensional curve of data when the wing and sensor of an flapping-wing aircraft with a wing installation angle of 0° are positioned 100mm above the wing.

[0032] Figure 8 It is a three-dimensional curve of data when the wing and sensor of a flapping-wing aircraft with a wing installation angle of 0° are 200mm below the wing;

[0033] Figure 9 It is a three-dimensional curve of data when the wings of an flapping-wing aircraft with a wing installation angle of 10° are aligned with the sensor.

[0034] Figure 10 This is a 3D graph of data from an ornithopter with a 10° wing angle, where the wing and sensor are positioned 100mm above the wing.

[0035] Figure 11 This is a three-dimensional curve of data when the wing and sensor of an flapping-wing aircraft with a wing installation angle of 10° are positioned 200mm below the wing.

[0036] Numbering on the map:

[0037] 10. Base; 10a. First slide rail; 10b. Second slide rail; 10b'. Sub-slide rail; 20. Clamping assembly; 21. Fixing frame; 211. Fixing plate; 212. Support rod; 22. Adjusting rod; 23. Left gripper; 24. Right gripper; 25. Force application handle; 26. Anti-slip texture; 30. Mounting component; 30a. First mounting component; 30b. Second mounting component; 30c. Third mounting component; 31. First mounting rod; 32. Second mounting rod; 33. Adjusting component; 34. Fastener; 40. Sensor; 50. Mounting hole; Detailed Implementation

[0038] To provide a clearer understanding of the technical features, objectives, and effects of this invention, specific embodiments are now described in detail with reference to the accompanying drawings. In the following description, it should be understood that the orientations or positional relationships indicated by terms such as "front," "rear," "upper," "lower," "left," "right," "longitudinal," "horizontal," "vertical," "horizontal," "top," "bottom," "inner," "outer," "head," and "tail" are based on the orientations or positional relationships shown in the accompanying drawings, and are constructed and operated in a specific orientation. They are only for the convenience of describing this technical solution and do not indicate that the device or element referred to must have a specific orientation; therefore, they should not be construed as limitations on this invention.

[0039] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," "linking," and "attachment" 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 direct connection or an indirect connection through an intermediate medium; and they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0040] The specific embodiments of the present invention will be described in further detail below with reference to the accompanying drawings and examples. The following examples are for illustrative purposes only and are not intended to limit the scope of the invention.

[0041] Figure 1 This is a top view of the test device for the flapping-wing aircraft according to an embodiment of this application; Figure 2 This is a schematic diagram of the structure of the test device for the flapping-wing aircraft according to an embodiment of this application. (Refer to...) Figure 1 and Figure 2 As shown, this disclosure provides a testing device for a flapping-wing aircraft, which includes a base 10, a clamping assembly 20, at least one mounting component 30, and a sensor 40.

[0042] Specifically, the base 10 has a first slide rail 10a and a plurality of spaced second slide rails 10b on its surface, the second slide rails 10b being perpendicular to the first slide rail 10a; each second slide rail 10b includes a sub-slide rail 10b' symmetrically arranged relative to the first slide rail 10a, the sub-slide rail 10b' being connected to the first slide rail 10a; a clamping assembly 20 is disposed on the surface of the base 10 for clamping the flapping-wing aircraft to be tested; a mounting member 30 is retractably disposed on the surface of the base 10 and is capable of moving along the first slide rail 10a and the sub-slide rails 10b'; a sensor 40 is installed at the end of each mounting member 30 away from the base 10 for detecting the wind speed of the flapping-wing aircraft to be tested clamped on the clamping assembly 20.

[0043] The flapping-wing aircraft testing device based on the above-mentioned technical features uses a clamping assembly 20 to clamp the flapping-wing aircraft to be tested. Then, a mounting component 30 with a sensor 40 is placed on a base 10. The position of the mounting component 30 on the base 10 is adjusted by using a first slide rail 10a and a sub-slide rail 10b' provided on the base 10, thereby adjusting the test position of the sensor 40. At the same time, the test height of the sensor 40 can be adjusted by extending and retracting the mounting component 30, thereby obtaining the wind field value of the flapping-wing aircraft. This allows for an effective evaluation of whether the airflow direction and wind volume generated by the flapping wing are reasonable, facilitating the adjustment of the structure and design by the R&D personnel based on the test results, reducing the R&D difficulty and shortening the R&D cycle.

[0044] For example, since the thermoelectric potential of a thermal anemometer is a fixed value when it is in still air (wind speed is zero), when measuring wind speed, the airflow causes the temperature of the thermocouple's operating environment to drop, and the thermoelectric potential across the thermocouple changes. This change is a function of the wind speed, and therefore the corresponding wind speed value can be calculated by measuring the thermoelectric potential. Compared to other sensors, the thermal anemometer can better acquire the wind speed of flapping-wing aircraft. Therefore, in this embodiment, the sensor 40 is preferably a thermal anemometer.

[0045] Reference Figure 2 In one embodiment, the mounting component 30 is provided with three components, namely a first mounting component 30a, a second mounting component 30b and a third mounting component 30c, wherein, when testing the flapping-wing aircraft holding the clamping assembly 20, the first mounting component 30a, the second mounting component 30b and the third mounting component 30c are located on the same straight line.

[0046] For example, different wing installation angles will cause flapping-wing aircraft to generate different airflow directions, thus affecting the flight state of the flapping-wing aircraft. Therefore, it is necessary to test the flight state of the flapping-wing aircraft's wings at different installation angles. In this embodiment, by setting an adjustable first mounting member 30a, a second mounting member 30b, and a third mounting member 30c on the base, and installing sensors 40 on each of the first mounting member 30a, the second mounting member 30b, and the third mounting member 30c, and by adjusting the distances from the first mounting member 30a, the second mounting member 30b, and the third mounting member 30c to the clamping assembly 20, as well as their height positions, wind field values ​​of the flapping-wing aircraft at different heights at the same location (e.g., when the sensor is level with the flapping-wing aircraft, when the sensor is above the flapping-wing aircraft, and when the sensor is below the flapping-wing aircraft) can be obtained, thereby effectively evaluating whether the airflow direction and wind volume generated by the flapping-wing are reasonable.

[0047] Figure 3 This is a schematic diagram of the mounting components in the test apparatus of the flapping-wing aircraft according to an embodiment of this application. (Refer to...) Figure 3 In one embodiment, the mounting member 30 includes a first mounting rod 31 and a second mounting rod 32. The second mounting rod 32 is retractably disposed within the first mounting rod 31. The sensor 40 is detachably connected to the end of the second mounting rod 32 away from the base 10. The end of the first mounting rod 31 facing the base 10 extends into the first slide rail 10a or the sub-slide rail 10b'.

[0048] For example, the second mounting rod 32 is retractably disposed within the first mounting rod 31, and then the sensor 40 is detachably connected to the end of the second mounting rod 32 away from the base 10. According to the test requirements of different heights (e.g., the sensor is level with the flapping-wing aircraft, the sensor is above the flapping-wing aircraft, or the sensor is below the flapping-wing aircraft), the height at which the second mounting rod 32 retracts into the first mounting rod 31 can be changed, thereby adjusting the height position of the sensor 40. At the same time, the position of the sensor 40 can also be adjusted by moving the position of the first mounting rod 31 within the first slide rail 10a or the sub-slide rail 10b' to meet the test requirements at different positions.

[0049] In addition, it should be noted that, in addition to the retractable connection method of the first mounting rod 31 and the second mounting rod 32 used in the above embodiment, the mounting component 30 can also be made by sequentially telescopically connecting multiple mounting rods, as long as the height of the sensor can be adjusted, there is no limitation on this.

[0050] Reference Figure 3 In one embodiment, it further includes an adjusting member 33, which is located on the outer side of the end of the first mounting rod 31 away from the base 10, and is used to adjust the length of the second mounting rod 32 when it retracts into the first mounting rod 31.

[0051] For example, when the height of the sensor needs to be adjusted, the adjusting member 33 is rotated to release the adjusting member 33 and lock the second mounting rod 32 that has retracted into the first mounting rod 31. Then, the length of the second mounting rod 32 retracted into the first mounting rod 31 is adjusted, thereby changing the height position of the sensor 40 mounted on the second mounting rod 32. This meets the testing requirements of the flapping-wing aircraft under test at different height positions. The structure is simple and the adjustment is convenient.

[0052] Reference Figure 3 In one embodiment, a fastener 34 is also included, which is sleeved on the end of the first mounting rod 31 facing the base 10 for locking the first mounting rod 31 onto the base 10.

[0053] For example, when adjusting the sensor 40 to the test position, the fastener 34 fitted onto the end of the first mounting rod 31 facing the base 10 can be tightened to lock it in place, thereby fixing the first mounting rod 31 onto the base 10. When it is necessary to adjust the position of the sensor 40, simply loosen the fastener 34 to release it from the lock on the first mounting rod 31, and then move the first mounting rod 31 to the position of the first slide rail 10a or the sub-slide rail 10b', thereby adjusting the position of the sensor 40 to meet different test position requirements. Alternatively, the fastener 34 can be a lock nut; there is no limitation on this.

[0054] Figure 4 This is a schematic diagram of the clamping assembly in the testing device for an flapping-wing aircraft according to an embodiment of this application. (Refer to...) Figure 4 In one embodiment, the clamping assembly 20 includes a fixing frame 21, an adjusting rod 22, a left gripper 23, and a right gripper 24. The fixing frame 21 is fixed to the surface of the base 10, the left gripper 23 is fixed to the fixing frame 21, and the right gripper 24 is sleeved on the adjusting rod 22, with one end of the adjusting rod 22 rotatably connected to the left gripper 23. When the adjusting rod 22 rotates, the right gripper 24 is driven to move closer to or away from the left gripper 23.

[0055] For example, the adjusting rod 22 can be a screw, or other components that can drive the right gripper 24 to move by rotating on its own; there is no particular limitation in this regard. In this embodiment, preferably, the adjusting rod 22 is a screw, and a slider (not shown) is connected to the lower part of the right gripper 24. The slider has a threaded hole that meshes with the screw. By driving the screw to rotate, the slider is driven to move on the screw, thereby causing the right gripper 24 to move closer to or away from the left gripper 23, thereby realizing the distance adjustment between the left gripper 23 and the right gripper 24. This satisfies the need to clamp flapping-wing aircraft of different sizes, with a simple structure and convenient adjustment.

[0056] Furthermore, the adjustment rod 22 can be rotated manually or by a power source; there is no particular limitation on which method is used. In this embodiment, preferably, a force-applying handle 25 is provided at the end of the adjustment rod 22 away from the left gripper 23, which allows the operator to easily drive the adjustment rod 22 to rotate.

[0057] Furthermore, anti-slip textures 26 are provided on the surfaces of the left gripper 23 and the right gripper 24 facing each other. The anti-slip textures 26 are used to increase the friction when in contact with the flapping-wing aircraft, and to prevent the left gripper 23 and the right gripper 24 from slipping relative to each other when the flapping-wing aircraft under test is held for too long, which would affect the accuracy of the test.

[0058] Reference Figure 4 In one embodiment, the fixing frame 21 includes a fixing plate 211 and multiple support rods 212. One end of the support rod 212 is connected to the surface of the base 10, the fixing plate 211 is installed on the other end of the support rod 212, the left gripper 23 is fixedly connected to the fixing plate 211, and the adjusting rod 22 is located above the fixing plate 211.

[0059] It should be noted that "multiple" refers to two or more support rods 212, and the specific number of support rods 212 needs to be determined according to the actual situation. For example, if two support rods 212 are set, they are arranged diagonally to support the fixing plate 211; if four support rods 212 are set, each pair of the four support rods 212 is symmetrically distributed, which can provide better support for the fixing plate 211 and avoid affecting the test results due to insufficient stability of the fixing plate 211 during the test.

[0060] Figure 5 This is a schematic diagram of the base structure in the test device for the flapping-wing aircraft according to an embodiment of this application. (Refer to...) Figure 5 In one embodiment, the surface of the base 10 has multiple mounting holes 50, and multiple support rods 212 extend into each mounting hole 50 to allow the support rods 212 to be detachably connected to the base 10. Thus, one end of the support rod 212 extending towards the base 10 is inserted into the mounting hole 50, and then a locking element (e.g., a nut) is used to lock the portion of the support rod 212 inserted into the mounting hole 50, thereby fixing the support rod 212 to the base 10. This design is simple and easy to assemble and disassemble.

[0061] This application also provides a testing method for a flapping-wing aircraft, the method comprising the following steps:

[0062] S10. Clamp the flapping-wing aircraft to be tested and set up multiple sensors at the same height and in a straight line behind the flapping-wing aircraft; one sensor is located directly behind the flapping-wing aircraft, and two sensors are located at the midpoints of the two wings of the flapping-wing aircraft respectively.

[0063] S20. Control the flapping-wing aircraft to fly according to preset motion parameters; wherein, the motion parameters include flapping frequency and flapping amplitude;

[0064] S30. Adjust the position of the sensor to test and record the wind speed of the flapping-wing aircraft under test at different wing angles.

[0065] In this embodiment, the flapping-wing aircraft to be tested is clamped and fixed. Then, multiple sensors are set at the rear of the flapping-wing aircraft. One sensor is located directly behind the flapping-wing aircraft, and two sensors are located at the midpoints of the two wings of the flapping-wing aircraft, respectively. The sensors are at the same height and on the same straight line. Then, the flapping-wing aircraft is controlled to fly with preset motion parameters to simulate the flight state of the flapping-wing aircraft. Next, the wing angle of the flapping-wing aircraft is adjusted so that the wind speed of the flapping-wing aircraft at different wing angles can be obtained by the sensors. Based on the obtained data, the optimal wing installation angle can be determined, which can effectively evaluate whether the airflow direction and wind volume generated by the flapping wing are reasonable. This allows the R&D personnel to adjust the structure and design based on the test results, reducing the R&D difficulty and shortening the R&D cycle.

[0066] For example, the testing method for the flapping-wing aircraft in this embodiment can be performed using the aforementioned testing device for flapping-wing aircraft, or other testing devices can be used. To facilitate the description of the specific testing method, the aforementioned testing device for flapping-wing aircraft is used to test a flapping-wing aircraft with a wingspan of 1.2m and wing installation angles of 0° and 10°, and three sensors are used as an example for illustration, but it is not limited to this.

[0067] A flapping-wing aircraft with a 0° wing mounting angle is fixed to the clamping assembly 20. The position of the mounting piece 30 on the base 10 is then adjusted so that three sensors located directly behind the flapping-wing aircraft and at the midpoint of the two wings are positioned 220mm behind the wings. The heights of the three sensors 40 are then adjusted sequentially to be flush with the wings, 100mm above the wings, and 200mm below the wings, respectively, to obtain the wind speed at three different altitudes at a distance of 220mm from the wings. The three sensors 40 are then adjusted to positions of 420mm and 720mm from the wings, and the height adjustments are repeated to obtain the wind speed at three different altitudes at these same distances. This yields the wind speed data for the flapping-wing aircraft with a 0° wing mounting angle at each test point, and a three-dimensional graph is exported (refer to...). Figures 6 to 8 ).

[0068] Similarly, a flapping-wing aircraft with a 10° wing mounting angle is fixed to the clamping assembly 20. Then, the position of the base 10 of the mounting component 30 is adjusted so that the three sensors 40, located directly behind the flapping-wing aircraft and at the midpoints of the two wings, are positioned 220mm, 420mm, and 720mm behind the wings. This height adjustment is repeated to obtain wind speed data at different heights (220mm, 420mm, and 720mm) behind the wings. This yields wind speed data for the flapping-wing aircraft with a 10° wing mounting angle at the aforementioned test points, and a three-dimensional graph is exported (refer to...). Figures 9 to 11 ).

[0069] Reference Figures 6 to 10 It can be concluded without a doubt that, compared to an ornithopter with a 0° wing angle, an ornithopter with a 10° wing angle experiences increased wind speed below the wing and decreased wind speed behind it. This suggests that the ornithopter with a 10° wing angle cannot generate sufficient thrust during flight, making it prone to pitching up. Therefore, based on test results, the developers designed the wing angle to be 0°.

[0070] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and substitutions can be made without departing from the technical principles of the present invention, and these improvements and substitutions should also be considered within the scope of protection of the present invention.

Claims

1. A testing device for flapping-wing aircraft, characterized in that, a base having a first slide and a plurality of second slides arranged at intervals on a surface thereof, the second slides being perpendicular to the first slide; wherein each of the second slides comprises a sub-slide arranged symmetrically relative to the first slide, the sub-slide being in communication with the first slide; a clamping assembly arranged on the surface of the base for clamping a flapping-wing aircraft to be tested; at least one mounting member telescopically arranged on the surface of the base and capable of moving along the first slide and the sub-slide; a sensor mounted at an end of each of the mounting members away from the base for detecting the wind speed of the flapping-wing aircraft to be tested clamped on the clamping assembly; the mounting member is provided with three, namely a first mounting member, a second mounting member and a third mounting member, wherein, in the case of testing the flapping-wing aircraft on the clamping assembly, the first mounting member, the second mounting member and the third mounting member are located on the same straight line; wherein one sensor is located at a position directly behind the flapping-wing aircraft, and two sensors are respectively located at the midpoint positions of the wings on both sides of the flapping-wing aircraft.

2. The flapping-wing aircraft testing apparatus according to claim 1, wherein the mounting member comprises a first mounting rod and a second mounting rod, the second mounting rod being telescopically arranged in the first mounting rod, the sensor being detachably connected at an end of the second mounting rod away from the base, and an end of the first mounting rod towards the base extending into the first slide or the sub-slide.

3. The flapping-wing aircraft testing apparatus according to claim 2, wherein Further comprising an adjusting member arranged outside an end of the first mounting rod away from the base for adjusting the length of the second mounting rod telescoped into the first mounting rod.

4. The flapping-wing aircraft testing apparatus according to claim 2, wherein Further comprising a fastener sleeved at an end of the first mounting rod towards the base for locking the first mounting rod on the base.

5. The flapping-wing aircraft testing apparatus according to claim 1, wherein the clamping assembly comprises a fixed frame, an adjusting rod, a left clamping jaw and a right clamping jaw, the fixed frame being fixed on the surface of the base, the left clamping jaw being fixed on the fixed frame, the right clamping jaw being sleeved on the adjusting rod, and an end of the adjusting rod being rotatably connected with the left clamping jaw; wherein, in the case of rotating the adjusting rod, the right clamping jaw is driven to approach or move away from the left clamping jaw.

6. The flapping-wing aircraft testing apparatus according to claim 5, wherein the fixed frame comprises a fixed plate and a plurality of support rods, one end of the support rods being connected with the surface of the base, the fixed plate being mounted at the other end of the support rods, the left clamping jaw being fixedly connected with the fixed plate, and the adjusting rod being located above the fixed plate.

7. The apparatus of claim 6, wherein: a plurality of mounting holes are formed on the surface of the base, and a plurality of the support rods extend into the mounting holes so that the support rods are detachably connected with the base.

8. The flapping-wing aircraft testing apparatus according to claim 1, wherein the sensor comprises a thermal wind speed sensor.

9. A method of testing a flapping-wing aircraft, characterized by, a method for testing a flapping-wing aircraft using the testing device of any one of claims 1 to 8, the method comprising the steps of: The flapping wing aircraft to be tested is clamped, and a plurality of sensors at the same height and on the same line are arranged behind the flapping wing aircraft; one sensor is located at the position directly behind the flapping wing aircraft, and two sensors are respectively located at the midpoint positions of the wings on both sides of the flapping wing aircraft. The flapping wing aircraft is controlled to fly at preset motion parameters; the motion parameters include flapping frequency and flapping amplitude. The positions of the sensors are adjusted to test the wind speed of the flapping wing aircraft in different wing angle states and record the wind speed.

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