Platform for testing pulling force and flight attitude of unmanned aerial vehicle

Abstract

The invention discloses an unmanned aerial vehicle tension and flight attitude test platform, which comprises a frame, the inner bottom surface of which is connected with a mounting plate; the upper end of the tension plate is connected with a first cylinder; the tension and compression sensor is arranged between the mounting plate and the tension plate; the upper end of the fixing plate is provided with a fixing part used for limiting the unmanned aerial vehicle, the bottom of the fixing plate is connected with a second cylinder part coaxial with the first cylinder part, and the fixing plate is movably arranged above the tension plate through cooperation of the first cylinder part and the second cylinder part; by adopting the test platform, the output results of the unmanned aerial vehicle under different input instruction signals can be safely and accurately tested, and the test states of pure tension and tension and posture combination can be switched by adjusting the length of each zipper.

Description

Technical Field

[0001] The invention belongs to the technical field of test tooling, and in particular relates to a UAV tension and flight attitude test platform. Background Art

[0002] Unmanned aerial vehicle (UAV) is an unmanned aircraft that is controlled by a radio remote control device and a self-contained program control device, or is operated completely or intermittently autonomously by an onboard computer.

[0003] During the development of drones, control programs need to be tested and optimized to achieve the best flight conditions. However, during the testing process, the drone may not operate as expected due to program errors, structural defects, and other reasons, posing the risk of personal injury and property damage. To this end, a tooling test platform is proposed that can observe the operating status while restricting the movement of the drone, thereby avoiding the above risks. Summary of the Invention

[0004] In order to solve the above technical problems, the present invention adopts the following technical solutions: A UAV tension and flight attitude test platform, comprising: A frame having a mounting plate connected to its inner bottom surface; A tension plate, the upper end of which is connected to a first cylinder; A tension and compression sensor is provided between the mounting plate and the tension plate; A fixing plate, wherein a fixing member for limiting the position of the drone is provided at the upper end of the fixing plate, and a second cylinder member coaxially arranged with the first cylinder member is connected to the bottom of the fixing plate. Through the cooperation of the first cylinder member and the second cylinder member, the fixing plate can be movably arranged above the tension plate; Zippers, the fixed plate is connected to the tension plate through a plurality of zippers; When the fixing plate moves away from the tension plate to a maximum distance, the plurality of zippers are in a taut state.

[0005] Furthermore, the first cylinder is sleeved on the outer circumference of the second cylinder.

[0006] Furthermore, a ball head is provided at the end of the second cylinder.

[0007] Furthermore, a spring is provided inside the first cylinder near the tension plate, and a free end of the spring is connected to a pressing piece that can act on the end of the second cylinder.

[0008] Furthermore, a plurality of lifting rings are provided on the opposite sides of the tension plate and the fixed plate.

[0009] Furthermore, flanges are connected to the tension plate and the fixed plate.

[0010] Furthermore, a rubber shock-absorbing ring is provided at the connection between the lower end of the fixing plate and the second cylinder.

[0011] Furthermore, the zipper comprises a metal chain.

[0012] Furthermore, at least one of the first cylinder and the second cylinder is made of aluminum.

[0013] Furthermore, a display screen electrically connected to the tension and compression sensors is provided on the frame, and the display screen cover is provided with a rainproof box.

[0014] Compared with the prior art, the present invention has the following beneficial effects: This test platform can safely and accurately test the output results of drones under different input command signals. By adjusting the length of each zipper, it is possible to switch between pure tension and combined tension and posture test states. This test platform limits some of the UAV's degrees of freedom, avoiding unforeseen losses caused by the UAV's out-of-control state while meeting the test requirements, which is conducive to reducing R&D costs and shortening the R&D cycle. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 A schematic diagram of the overall structure of a specific embodiment of the present invention; Figure 2 A schematic diagram of a partial structure of a specific embodiment of the present invention (viewpoint 1); Figure 3 A schematic diagram of a partial structure of a specific embodiment of the present invention (viewpoint 2); Figure 4 A schematic cross-sectional view showing a specific embodiment of the present invention; Figure 5 A schematic diagram of an explosion structure embodying a specific embodiment of the present invention; Figure 6 A schematic diagram of the local structure of a specific embodiment of the present invention (viewpoint three); The reference numerals in the drawings of the specification include: Frame 1, mounting plate 2, tension and compression sensor 20, tension plate 21, first cylinder 3, spring 30, pressing piece 31, fixing plate 4, fixing part 40, second cylinder 5, ball head 50, zipper 6, hanging ring 7, flange 8, rubber shock-absorbing ring 80, rainproof box 9. DETAILED DESCRIPTION

[0016] In order to enable those skilled in the art to better understand the present invention, the technical solution of the present invention is further described below with reference to the accompanying drawings and embodiments.

[0017] The accompanying drawings are for illustrative purposes only and are schematic diagrams, not actual drawings, and should not be construed as limiting this patent. To better illustrate the embodiments of the present invention, certain components of the drawings may be omitted, enlarged, or reduced, and do not represent the dimensions of actual products. It is understandable to those skilled in the art that certain well-known structures and their descriptions may be omitted from the drawings. Identical or similar reference numerals in the drawings of the embodiments of the present invention correspond to identical or similar components. In the description of the present invention, it should be understood that the terms "upper," "lower," "left," "right," "inner," "outer," and the like, indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the drawings and are intended only to facilitate the description of the present invention and simplify the description. They do not indicate or imply that the devices or components referred to must have specific orientations, be constructed, or operate in specific orientations. Therefore, the terms describing positional relationships in the drawings are for illustrative purposes only and should not be construed as limiting this patent. Those skilled in the art will understand the specific meanings of the above terms based on specific circumstances.

[0018] like Figure 1 - Figure 6 As shown, a UAV tension and flight attitude test platform of the present invention includes a frame 1, a tension plate 21, a tension and compression sensor 20, a fixing plate 4 and a zipper 6; Among them, the inner bottom surface of the frame 1 is connected with a mounting plate 2; The upper end of the tension plate 21 is connected to the first cylinder 3; The tension and compression sensor 20 is arranged between the mounting plate 2 and the tension plate 21; A fixing member 40 for limiting the position of the drone is provided at the upper end of the fixing plate 4. A second cylinder member 5 coaxially arranged with the first cylinder member 3 is connected to the bottom of the fixing plate 4. Through the cooperation of the first cylinder member 3 and the second cylinder member 5, the fixing plate 4 can be movably arranged above the tension plate 21. The fixing plate 4 is connected to the tension plate 21 via a plurality of zippers 6; When the fixing plate 4 moves to the maximum distance away from the tension plate 21 , the plurality of zippers 6 are in a taut state.

[0019] The first cylinder 3 and the second cylinder 5 form a plunger-type motion pair. The frame 1 fixes the tension and compression sensor 20. The plunger-type motion pair and the UAV fixing seat are arranged above the tension and compression sensor 20. The plunger-type motion pair is a clearance fit, and its stroke is limited by the tension / steel chain.

[0020] Frame 1 is made of European standard aluminum profiles, and its profile parameters and length can be adjusted according to the parameters of the target UAV.

[0021] Frame 1 is reinforced with diagonal braces and stringers to overcome deformation caused by the drone's tension. Aluminum mounting plates 2 are used to secure frame 1 to the tension and compression sensors 20, constraining frame 1's displacement while providing a horizontal mounting platform.

[0022] The tension and compression sensor 20 is fixed on the mounting platform, and a steel sensor flange is used above to be threadedly connected to the tension and compression sensor 20, so that the flange can be easily disassembled to replace the upper components.

[0023] An aluminum tension plate 21 is sequentially installed on the flange. The tension plate 21 is provided with M8 through holes, a lower flange, an aluminum tube, an upper flange, and a rubber shock-absorbing ring 80 on all sides.

[0024] This test platform allows for safe and accurate testing of drone outputs under varying input command signals. By adjusting the length of each zipper (6), it allows switching between pure tension and combined tension and posture testing. This test platform restricts some of the drone's degrees of freedom, avoiding unforeseen losses in the event of a loss of control while still meeting testing requirements. This helps reduce R&D costs and shortens development cycles.

[0025] The first cylinder 3 can be sleeved on the outer periphery of the second cylinder 5, or the two can be interchanged. The second cylinder 5 is on the outer periphery of the first cylinder 3, and its function is not affected.

[0026] Specifically, in this embodiment, the outer diameter of the second cylinder member 5 is smaller than the inner diameter of the first cylinder member 3. A ball head 50 is provided at the end of the second cylinder member 5, and the diameter of the ball head 50 is slightly smaller than the inner diameter of the first cylinder member 3.

[0027] A plurality of fixing members 40 are arranged at the four corners of the fixing plate 4. The fixing members 40 adopt pipe clamps with clamping functions and are used to fix the drone. There are M8 through holes at the four corners.

[0028] A ball head 50 is provided at the end of the second cylindrical member 5 .

[0029] Turn the ball head 50 downward and use four pull / iron chains and M8 lifting rings 7 to connect the two plates with M8 holes to limit the vertical displacement distance of the above components.

[0030] The fixing plate 4 and the fixing part 40 above the steel sensor flange have different size combinations to adapt to drones of different sizes.

[0031] In addition, a spring 30 is provided inside the first cylinder 3 near the tension plate 21 , and a free end of the spring 30 is connected to a pressing piece 31 that can act on the end of the second cylinder 5 .

[0032] A rubber shock-absorbing ring 80 is provided at the connection between the lower end of the fixing plate 4 and the second cylinder 5. After the UAV test is completed, the second cylinder 5 and the fixing plate 4 fall down. The rubber shock-absorbing ring 80, the spring 30 and the pressing plate 31 prevent the entire test platform from being rigidly impacted and damaged.

[0033] Specifically, a plurality of lifting rings 7 are provided on the opposite sides of the tension plate 21 and the fixing plate 4 .

[0034] Flanges 8 are connected to the tension plate 21 and the fixed plate 4. Two flanges 8 are provided, one on the upper and one on the lower.

[0035] The zipper 6 can be made of a metal chain, or a plastic or rubber rope made of a soft material. In this embodiment, an aluminum metal zipper 6 is used.

[0036] In order to reduce the overall weight of the test platform, at least one of the first cylinder 3 and the second cylinder 5 is made of aluminum.

[0037] A display screen electrically connected to the tension and compression sensor 20 is provided on the frame 1 , and a rainproof box 9 is provided on the display screen cover.

[0038] A rainproof box 9 is provided outside the frame 1, a digital display screen is placed inside, and a tension and compression sensor 20 is connected to read the readings.

[0039] During operation, the drone's legs are secured to the mounting member 40. The drone is started and the power is increased. The drone drives the mounting plate 4 and the second pipe upward. When the ball head 50 is about to reach a certain height, the tension / steel chain is tightened to prevent the drone from ascending further. The drone can then be operated independently, its flight status monitored, and the tension displayed on the digital display. When the tension is reduced, the upper flange contacts the rubber shock-absorbing ring 80, and the drone is safely reset.

[0040] When the drone drives the fixed plate 4 structure to rise until the steel chain is straightened, all the tension is transmitted to the tension plate 21 through the steel / zipper 6, and then to the tension and compression sensor 20 through the lower flange. The tension can be viewed on the digital display screen. At the same time, the ball head 50 rises to the top of the first pipe fitting, giving it rotational freedom, and under the constraint of the steel chain, the second pipe fitting will not fall out of the first pipe fitting.

[0041] The above are only embodiments of the present invention. Common knowledge such as the known specific structures and characteristics in the scheme is not described in detail here. Ordinary technicians in the relevant field are aware of all common technical knowledge in the technical field of the invention before the application date or priority date, can obtain all existing technologies in the field, and have the ability to apply conventional experimental means before that date. Ordinary technicians in the relevant field can improve and implement this scheme in combination with their own abilities under the guidance of this application. Some typical known structures or known methods should not become obstacles for ordinary technicians in the relevant field to implement this application. It should be pointed out that for those skilled in the art, without departing from the structure of the present invention, several variations and improvements can be made, which should also be regarded as the scope of protection of the present invention. These will not affect the effect of the implementation of the present invention and the practicality of the patent.

Claims

1. A UAV tension and flight attitude test platform, characterized by: include: A frame (1) having an inner bottom surface connected to a mounting plate (2); A tension plate (21), the upper end of which is connected to a first cylinder (3); A tension and compression sensor (20) is arranged between the mounting plate (2) and the tension plate (21); A fixing plate (4), wherein a fixing member (40) for limiting the position of the drone is provided at the upper end of the fixing plate (4), and a second cylinder member (5) coaxially arranged with the first cylinder member (3) is connected to the bottom of the fixing plate (4); through the cooperation of the first cylinder member (3) and the second cylinder member (5), the fixing plate (4) can be movably arranged above the tension plate (21); zippers (6), the fixing plate (4) is connected to the tension plate (21) via a plurality of zippers (6); When the fixing plate (4) moves to a maximum distance away from the tension plate (21), the plurality of zippers (6) are in a taut state.

2. The UAV tension and flight attitude testing platform according to claim 1, characterized in that: The first cylinder (3) is sleeved on the outer circumference of the second cylinder (5).

3. The UAV tension and flight attitude testing platform according to claim 2, characterized in that: A ball head (50) is provided at the end of the second cylinder (5).

4. The UAV tension and flight attitude testing platform according to claim 2 or 3, characterized in that: A spring (30) is provided inside the first cylinder (3) on one side close to the tension plate (21), and a free end of the spring (30) is connected to a pressing piece (31) that can act on the end of the second cylinder (5).

5. The UAV tension and flight attitude testing platform according to claim 1, 2 or 3, characterized in that: A plurality of lifting rings (7) are provided on the opposite side of the tension plate (21) and the fixed plate (4).

6. The UAV tension and flight attitude testing platform according to claim 1, characterized in that: The tension plate (21) and the fixed plate (4) are both connected with flanges (8).

7. The UAV tension and flight attitude test platform according to claim 1, 2, 3 or 6, characterized in that: A rubber shock-absorbing ring (80) is provided at the connection between the lower end of the fixing plate (4) and the second cylinder (5).

8. The UAV tension and flight attitude testing platform according to claim 1, characterized in that: The zipper (6) comprises a metal chain.

9. The UAV tension and flight attitude testing platform according to claim 1, characterized in that: At least one of the first cylinder (3) and the second cylinder (5) is made of aluminum.

10. The UAV tension and flight attitude testing platform according to claim 1, characterized in that: A display screen electrically connected to the tension and compression sensor (20) is provided on the frame (1), and the display screen cover is provided with a rainproof box (9).

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