An intensity detection device for a landing bracket of a drone

Abstract

The present invention belongs to the technical field of drone landing bracket detection, and specifically refers to a strength detection device for a drone landing bracket, which includes a frame body. The top wall of the frame body is fixedly connected with telescopic rods in a rectangular array, and the other ends of the telescopic rods are fixedly connected with a box body. The top wall of the frame body is connected with a pneumatic fixing component. A power component and a transmission component are connected inside the box body. The power component is connected with the pneumatic fixing component. A round box is rotatably connected to the bottom wall of the box body; this application uses mechanical transmission to compress the landing bracket, detect the impact resistance of the landing bracket during landing, continuously compress the landing bracket, and fix the landing bracket, simulating the state when the landing bracket contacts the ground during the landing of the drone. It can also be switched to the anti-twist detection of the landing bracket, and the multi-directional impact resistance of the landing bracket is detected during the twist detection, synchronously detecting the impact resistance, anti-twist performance and multi-directional impact resistance of the landing bracket.

Description

Technical Field

[0001] The present invention belongs to the technical field of unmanned aerial vehicle landing gear detection, and specifically refers to a strength detection device for the landing gear of an unmanned aerial vehicle. Background Art

[0002] Unmanned aerial vehicles play an increasingly important role in the modern aviation field. As a key component, its landing gear not only needs to withstand the impact during takeoff and landing, but also needs to maintain stability during flight. Therefore, it is crucial to accurately detect the strength of the landing gear of an unmanned aerial vehicle.

[0003] During the production process of the unmanned aerial vehicle landing gear, it is necessary to conduct sampling strength detection on the landing gear. However, the existing strength detection devices still have certain deficiencies. Traditional detection methods often can only perform mechanical tests in a single direction and cannot simulate the complex stress conditions suffered by the landing gear in reality. When changing the detection direction in traditional detection methods, errors are likely to occur and the data is likely to be inaccurate.

[0004] Therefore, a strength detection device for the landing gear of an unmanned aerial vehicle is needed to solve the technical problem that only mechanical tests in a single direction can be carried out in the prior art. Summary of the Invention

[0005] In view of the above situation, in order to overcome the defects of the prior art, the present invention provides a strength detection device for the landing gear of an unmanned aerial vehicle. This application uses a mechanical transmission method to press the landing gear tightly, detects the impact resistance of the landing gear during landing, and continuously presses the landing gear tightly. It can also use the downward pressure generated by the detection to fix the landing gear to prevent the landing gear from moving, simulating the state when the landing gear of the unmanned aerial vehicle contacts the ground during landing. The downward pressure can also be switched to the anti-twist detection of the landing gear, and the multi-directional impact resistance performance of the landing gear can be detected while detecting the twist. The impact resistance performance, anti-twist performance, and multi-directional impact resistance performance of the landing gear are detected synchronously, simulating the force-bearing situation of the landing gear under complex conditions, and solving the technical problem that only mechanical tests in a single direction can be carried out in the prior art.

[0006] To solve the above technical problems, the technical solution adopted by the present invention is as follows: A strength detection device for the landing gear of an unmanned aerial vehicle proposed in this solution includes a frame body. The top wall of the frame body is fixedly connected with telescopic rods in a rectangular array. The other ends of the telescopic rods are fixedly connected with a box body. The top wall of the frame body is connected with a pneumatic fixing component. A power component and a transmission component are connected inside the box body. The power component is connected with the pneumatic fixing component. The bottom wall of the box body is rotatably connected with a round box. A four-way pushing component is connected inside the round box. The four-way pushing component is connected with the power component. A pressing unit is connected to the box body, and the pressing unit is also connected to the frame body. When the power component is stationary, it is in transmission connection with the pressing unit. When the power component is moving, it is in transmission connection with the transmission component.

[0007] Preferably, the four-way pushing assembly includes a rotating disk, a first driving plate, a second driving plate and a support column. The rotating disk is coaxially and rotatably connected to the inner top wall of the circular box. A pushing column is eccentrically and fixedly connected to the bottom wall of the rotating disk. The first driving plate is symmetrically and slidably connected to the bottom wall of the circular box. The second driving plate is symmetrically and slidably connected to the bottom wall of the circular box. During the rotation of the pushing column, it contacts the first driving plate and the second driving plate in sequence. A first pushing plate is fixedly connected to the first driving plate. A second pushing plate is fixedly connected to the second driving plate. The first pushing plate and the second pushing plate penetrate the bottom wall of the circular box. The support column is coaxially and fixedly connected to the bottom wall of the circular box. Push springs are fixedly connected to the circumferential wall of the support column in a rectangular array. The opposite two sides of the push springs are respectively fixedly connected to the first pushing plate and the second pushing plate.

[0008] Preferably, the transmission assembly includes a transmission shaft, a transmission gear ring and a transmission synchronous belt. The top end of the transmission shaft is rotatably connected to the inner top wall of the box body. The other end of the transmission shaft rotatably penetrates the bottom wall of the box body and the top wall of the circular box and is coaxially fixedly connected to the rotating disk. And the protruding end of the transmission shaft is in frictional connection with the top wall of the circular box. The transmission gear ring is rotatably connected to the inner top wall of the box body. The transmission synchronous belt is sleeved on the top end of the transmission shaft and the transmission gear ring.

[0009] Preferably, the pressing unit includes a pressing gear ring and a screw rod. The pressing gear ring is rotatably connected to the inner bottom wall of the box body. The pressing gear ring is coaxially arranged with the transmission gear ring. One end of the screw rod rotatably penetrates the box body and is coaxially fixedly connected to the pressing gear ring. The screw rod is threadedly connected to the frame body.

[0010] Preferably, the power assembly includes a pneumatic lifting rod, a lifting plate and a bidirectional motor. The lifting plate is longitudinally slidably connected to the inner side wall of the box body. The base end of the pneumatic lifting rod is fixedly connected to the inner bottom wall of the box body. The output end of the pneumatic lifting rod is fixedly connected to the bottom wall of the lifting plate. A bidirectional motor is fixedly connected to the lifting plate. The bidirectional motor is coaxially arranged with the pressing gear ring and the transmission gear ring.

[0011] Preferably, the pneumatic fixing assembly includes an I-shaped frame, a vacuum box and a fixing plate. The bottom wall of the vacuum box is fixedly connected to the inner bottom wall of the frame body. The bottom of the I-shaped frame is longitudinally slidably connected to the inner side wall of the vacuum box. The middle of the I-shaped frame is longitudinally slidably connected to the frame body. The upper part of the I-shaped frame is located above the frame body. On both sides of the top wall of the upper part of the I-shaped frame, pneumatic push rods are symmetrically and fixedly arranged, and the output ends of the symmetrically arranged pneumatic push rods are arranged oppositely. The side wall of the fixing plate is fixedly connected to the output end of the pneumatic push rod. The top wall of the frame body is symmetrically and fixedly connected with compression springs. The other end of the compression spring is fixedly connected to the bottom wall of the upper part of the I-shaped frame. The side wall of the box body is fixedly communicated with an electric valve and a one-way valve. The base end of the pneumatic push rod is communicated with the side wall of the vacuum box through a pipeline. The side wall of the vacuum box is communicated with the base end of the pneumatic lifting rod through an air pipe. The electric valve is electrically connected to the bidirectional motor.

[0012] The beneficial effects achieved by the present invention with the above structure are as follows:

[0013] 1. The present application uses a mechanical transmission method to press the landing gear, detects the impact resistance when the landing gear descends, and continuously presses the landing gear. It can also use the downward pressure to compress air, and the compressed air fixes the landing gear to prevent the landing gear from moving. It simulates the state when the landing gear of the drone touches the ground during landing. The compressed air can also be switched to the anti-twist detection of the landing gear. During the twist detection, the multi-directional impact resistance of the landing gear is detected. The impact resistance, anti-twist performance and multi-directional impact resistance of the landing gear are detected synchronously, simulating the force condition of the landing gear under complex conditions;

[0014] 2. The screw is threadedly connected to the frame, driving the landing gear to be pressed on the I-shaped frame. The downward pressure is used to compress the air in the vacuum box, and the compressed air fixes the bottom of the landing gear to prevent the landing gear from shaking during detection. It simulates the state when the landing gear of the drone touches the ground during landing to detect the impact resistance of the landing gear. The round box and the I-shaped frame press the landing gear, and according to whether the landing gear is damaged, it is determined whether the landing gear is qualified;

[0015] 3. The compressed air in the vacuum box starts the pneumatic lifting rod. The pneumatic lifting rod drives the bidirectional motor to engage with the transmission gear ring, driving the transmission shaft to rotate. The transmission shaft is frictionally connected to the round box, driving the landing gear to rotate. Since the bottom of the landing gear is fixed, the landing gear is subjected to a twisting force, and the anti-twist performance of the landing gear is detected in the pressed state. According to whether the landing gear is damaged, it is determined whether the landing gear is qualified. When the landing gear is not damaged, the frictional connection between the transmission shaft and the round box fails;

[0016] 4. The drive shaft also drives the rotating disk to rotate. The rotating disk drives the push column to sequentially push the first driving plate and the first push plate, pushing the landing bracket in multiple directions. At this time, the bottom of the landing bracket is fixed, and the anti-deformation ability of the landing bracket when it is impacted in multiple directions is detected. The multi-directional anti-impact performance of the landing bracket is detected in the compressed and continuously twisted states. According to whether the landing bracket is deformed, it is determined whether the landing bracket is qualified. Brief Description of the Drawings

[0017] The drawings are used to provide a further understanding of the solution, and constitute a part of the specification. Together with the embodiments of the present invention, they are used to explain the present invention, and do not constitute a limitation to the present invention.

[0018] Figure 1 It is a schematic diagram of the overall structure of a device for detecting the strength of a landing bracket for an unmanned aerial vehicle proposed by the present invention;

[0019] Figure 2 It is a schematic diagram of the overall sectional structure of a device for detecting the strength of a landing bracket for an unmanned aerial vehicle proposed by the present invention;

[0020] Figure 3 It is a schematic diagram of the connection structure of the upper part of the circular box of a device for detecting the strength of a landing bracket for an unmanned aerial vehicle proposed by the present invention;

[0021] Figure 4 It is a schematic diagram of the connection structure of the lower part of the circular box of a device for detecting the strength of a landing bracket for an unmanned aerial vehicle proposed by the present invention;

[0022] Figure 5 It is a schematic diagram of the internal connection structure of the box body of a device for detecting the strength of a landing bracket for an unmanned aerial vehicle proposed by the present invention;

[0023] Figure 6 It is a schematic diagram of the connection structure of the frame body of a device for detecting the strength of a landing bracket for an unmanned aerial vehicle proposed by the present invention.

[0024] In the drawings: 1. Frame body, 2. Telescopic rod, 3. Box body, 4. Pneumatic fixing component, 6. Power component, 7. Transmission component, 8. Four-way pushing component, 9. Circular box, 62. Compression unit, 401. I-shaped frame, 402. Electric valve, 403. Vacuum box, 404. Check valve, 405. Pneumatic push rod, 406. Fixed plate, 408. Compression spring, 601. Pneumatic lifting rod, 602. Lifting plate, 603. Bidirectional motor, 607. Compression gear ring, 608. Screw rod, 701. Drive shaft, 702. Transmission gear ring, 703. Transmission synchronous belt, 801. Rotating disk, 802. Push column, 803. First driving plate, 804. First push plate, 805. Second driving plate, 806. Second push plate, 807. Push spring, 808. Support column.

[0025] The accompanying drawings are used to provide a further understanding of the present invention and form a part of the description. Together with the embodiments of the present invention, they are used to explain the present invention and do not constitute a limitation to the present invention. Detailed Embodiments

[0026] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts belong to the scope of protection of the present invention.

[0027] Embodiment 1, as Figures 1-6 shown, a strength detection device for a landing bracket of a drone proposed by this solution includes a frame 1. The top wall of the frame 1 is fixedly connected with telescopic rods 2 in a rectangular array. The other ends of the telescopic rods 2 are fixedly connected with a box body 3. The top wall of the frame 1 is connected with a pneumatic fixing component 4. A power component 6 and a transmission component 7 are connected in the box body 3. The power component 6 is connected with the pneumatic fixing component 4. The bottom wall of the box body 3 is rotatably connected with a round box 9. A four-way pushing component 8 is connected in the round box 9. The four-way pushing component 8 is connected with the power component 6. A pressing unit 62 is connected to the box body 3. The pressing unit 62 is also connected to the frame 1. When the power component 6 is stationary, it is in transmission connection with the pressing unit 62. When the power component 6 is moving, it is in transmission connection with the transmission component 7.

[0028] As Figures 1-4As shown, the four-way pushing component 8 includes a rotating disk 801, a first driving plate 803, a second driving plate 805, and a support column 808. The rotating disk 801 is coaxially and rotatably connected to the inner top wall of the circular box 9. An eccentric pushing column 802 is fixedly connected to the bottom wall of the rotating disk 801. The first driving plate 803 is symmetrically and slidably connected to the bottom wall of the circular box 9. The second driving plate 805 is symmetrically and slidably connected to the bottom wall of the circular box 9. The second driving plate 805 is perpendicular to the first driving plate 803. During the rotation of the pushing column 802, it contacts the first driving plate 803 and the second driving plate 805 in sequence, and the pushing column 802 also pushes the first driving plate 803 and the second driving plate 805 to move. A first pushing plate 804 is fixedly connected to the first driving plate 803, and a second pushing plate 806 is fixedly connected to the second driving plate 805. The first pushing plate 804 and the second pushing plate 806 penetrate the bottom wall of the circular box 9. The support column 808 is coaxially and fixedly connected to the bottom wall of the circular box 9. Push springs 807 are fixedly connected to the circumferential wall of the support column 808 in a rectangular array. The opposite two sides of the push springs 807 are respectively fixedly connected to the first pushing plate 804 and the second pushing plate 806. The rotating disk 801, the pushing column 802, the first driving plate 803, the first pushing plate 804, the second driving plate 805, the second pushing plate 806, the push springs 807, and the support column 808 are made of non-magnetic materials.

[0029] As Figures 1-2 and Figure 5 As shown, the transmission component 7 includes a transmission shaft 701, a transmission gear ring 702, and a transmission synchronous belt 703. The top end of the transmission shaft 701 is rotatably connected to the inner top wall of the box body 3. The other end of the transmission shaft 701 rotatably penetrates the bottom wall of the box body 3 and the top wall of the circular box 9 and is coaxially fixedly connected to the rotating disk 801, and the extended end of the transmission shaft 701 is in frictional connection with the top wall of the circular box 9. The transmission gear ring 702 is rotatably connected to the inner top wall of the box body 3. The transmission synchronous belt 703 is sleeved on the top end of the transmission shaft 701 and the transmission gear ring 702.

[0030] As Figures 1-2 and Figure 5 As shown, the pressing unit 62 includes a pressing gear ring 607 and a screw 608. The pressing gear ring 607 is rotatably connected to the inner bottom wall of the box body 3. The pressing gear ring 607 is coaxially arranged with the transmission gear ring 705. One end of the screw 608 rotatably penetrates the box body 3 and is coaxially fixedly connected to the pressing gear ring 607. The screw 608 is threadedly connected to the frame body 1.

[0031] As Figures 1-2 and Figure 5As shown, the power assembly 6 includes a pneumatic lifting rod 601, a lifting plate 602, and a bidirectional motor 603. The lifting plate 602 is longitudinally slidably connected to the inner side wall of the box body 3. The base end of the pneumatic lifting rod 601 is fixedly connected to the inner bottom wall of the box body 3, and the output end of the pneumatic lifting rod 601 is fixedly connected to the bottom wall of the lifting plate 602. A bidirectional motor 603 is fixedly connected to the lifting plate 602. The bidirectional motor 603 is coaxially arranged with a pressing tooth ring 607 and a transmission tooth ring 702. When the pneumatic lifting rod 601 is in the initial state, the bidirectional motor 603 is in transmission connection with the pressing tooth ring 607. When the pneumatic lifting rod 601 is started, the bidirectional motor 603 is in transmission connection with the transmission tooth ring 702.

[0032] As Figures 1-2 and Figures 5-6 As shown, the pneumatic fixing assembly 4 includes an I-shaped frame 401, a vacuum box 403, and a fixing plate 406. The bottom wall of the vacuum box 403 is fixedly connected to the inner bottom wall of the frame body 1. The bottom of the I-shaped frame 401 is longitudinally slidably connected to the inner side wall of the vacuum box 403. The middle of the I-shaped frame 401 is longitudinally slidably connected to the frame body 1. The upper part of the I-shaped frame 401 is located above the frame body 1. On both sides of the top wall of the upper part of the I-shaped frame 401, pneumatic push rods 405 are symmetrically and fixedly arranged, and the output ends of the symmetrically arranged pneumatic push rods 405 are arranged oppositely. The side wall of the fixing plate 406 is fixedly connected to the output end of the pneumatic push rod 405. On the top wall of the frame body 1, compression springs 408 are symmetrically and fixedly connected, and the other end of the compression spring 408 is fixedly connected to the bottom wall of the upper part of the I-shaped frame 401. The side wall of the box body 3 is fixedly communicated with an electric valve 402 and a one-way valve 404. The base end of the pneumatic push rod 405 is communicated with the side wall of the vacuum box 403 through a pipeline. The side wall of the vacuum box 403 is communicated with the base end of the pneumatic lifting rod 601 through an air pipe. The electric valve 402 is electrically connected to the bidirectional motor 603.

[0033] The landing bracket is placed on the top wall of the upper part of the I-shaped frame 401, and the bottom end of the landing bracket is located between the fixed plates 406 on both sides. The bidirectional motor 603 is started, pushing the clamping gear ring 607 to rotate, driving the screw 608 to rotate, and the screw 608 drives the box body 3 to approach the frame body 1. At the same time, the telescopic rod 2 is compressed. When the box body 3 drives the round box 9 to contact the top of the landing bracket, the top of the landing bracket and the bottom wall of the round box 9 are connected by an electromagnet. The round box 9 drives the bottom end of the I-shaped frame 401 to move in the vacuum box 403 by pushing the landing bracket, compressing the clamping spring 408, compressing the air in the vacuum box 403, and the air enters the pneumatic push rod 405. The push rod 405 is started, driving the fixing plate 406 close to the bottom of the landing bracket. The fixing plate 406 clamps and fixes the bottom of the landing bracket to prevent displacement of the bottom of the landing bracket, simulating the state of the landing bracket touching the ground when the drone lands, and the detection result is more accurate. At the same time, the round box 9 and the I-shaped frame 401 press the landing bracket to simulate the state of the landing bracket being subjected to impact force when the drone lands, and detect the impact resistance of the landing bracket. When the landing bracket is damaged under the impact, affecting the flight attitude of the drone, the landing bracket detection fails. When the landing bracket is not damaged under the impact and does not affect the flight attitude of the drone, the landing bracket detection passes.

[0034] When the air in the vacuum box 403 is compressed, the air enters the pneumatic lifting rod 601, the pneumatic lifting rod 601 starts, drives the lifting plate 602 close to the top wall of the box body 3, the lifting plate 602 drives the bidirectional motor 603 to move, the bidirectional motor 603 is separated from the pressing gear ring 607, and the screw 608 stops rotating. At this time, the round box 9 and the I-beam 401 continue to press the landing bracket, and at the same time the fixed plate 406 clamps the bottom of the landing bracket. The lifting plate 602 drives the bidirectional motor 603 to be connected with the transmission gear ring 702, the pneumatic lifting rod 601 stops, and the transmission gear ring 702 drives the transmission through the transmission synchronous belt 703 The shaft 701 rotates, and the transmission shaft 701 pushes the round box 9 to rotate, driving the top of the landing bracket to rotate. At this time, the fixing plate 406 clamps the bottom of the landing bracket, and the round box 9 and the I-shaped frame 401 continue to press the landing bracket, simulating the twisting force applied to the landing bracket when the drone lands, and testing the anti-twisting performance of the landing bracket. The landing bracket is damaged under twisting, affecting the flight attitude of the drone, and the landing bracket fails the test. The landing bracket is not damaged under twisting and will not affect the flight attitude of the drone. The landing bracket is qualified. When the landing bracket is qualified, the friction between the transmission shaft 701 and the round box 9 fails, and the twisting of the landing bracket stops;

[0035] The transmission shaft 701 also drives the rotating disk 801 to rotate, driving the pushing column 802 to rotate. The pushing column 802 sequentially pushes the first driving plate 803 and the second driving plate 805 closer to the support column 808. The first driving plate 803 and the second driving plate 805 respectively drive the first pushing plate 804 and the second pushing plate 806 to move. The first pushing plate 804 and the second pushing plate 806 sequentially come into contact with the upper part of the landing gear bracket, performing impact detection on four directions of the landing gear bracket. At this time, the fixing plate 406 clamps the bottom of the landing gear bracket, the circular box 9 and the I-beam 401 continuously press the landing gear bracket, and the transmission shaft 701 and the circular box 9 continuously twist the landing gear bracket. The landing gear bracket is damaged under multi-directional impact, affecting the flight attitude of the drone. The landing gear bracket fails the detection. When the landing gear bracket is not damaged under multi-directional impact and does not affect the flight attitude of the drone, the landing gear bracket passes the detection. A downward pressure, a twisting force, and a multi-directional impact force are applied to the landing gear bracket to simulate the force-bearing situation of the landing gear bracket under complex conditions;

[0036] When the detection is completed, the bidirectional motor 603 stops. At the same time, the electric valve 402 is started, and the air in the vacuum box 403 is discharged. The pneumatic lifting rod 601 and the pneumatic push rod 405 are reset. The pneumatic push rod 405 drives the fixing plate 406 to stop clamping the landing gear bracket. The pneumatic lifting rod 601 drives the bidirectional motor 603 to separate from the transmission gear ring 702. At the same time, the bidirectional motor 603 is in transmission connection with the pressing gear ring 607. The bidirectional motor 603 rotates in reverse, driving the screw 608 to rotate in reverse. The box body 3 moves away from the frame body 1, the landing gear bracket moves away from the moving plate 401, the compression spring 408 is reset, and external air is injected into the vacuum box 403 through the one-way valve 404. When the external air drives the screw 608 to reset, the bidirectional motor 603 stops, and the landing gear bracket is taken off.

[0037] The above describes the present invention and its implementation manners. Such description is not restrictive. What is shown in the drawings is only one of the implementation manners of the present invention, and the actual structure is not limited thereto. Generally speaking, if those of ordinary skill in the art are inspired by it and design similar structural manners and embodiments without creative efforts without departing from the gist of the present invention, they shall fall within the protection scope of the present invention.

Claims

1. An intensity detection device for a landing bracket of a drone, comprising a frame body (1), wherein the top wall of the frame body (1) is fixedly connected with telescopic rods (2) in a rectangular array, and the other ends of the telescopic rods (2) are fixedly connected with a box body (3), and it is characterized in that: A pneumatic fixing component (4) is connected to the top wall of the frame body (1). A power component (6) and a transmission component (7) are connected inside the box body (3). The power component (6) is connected to the pneumatic fixing component (4). The bottom wall of the box body (3) is rotatably connected to a circular box (9). A four-way pushing component (8) is connected inside the circular box (9). The four-way pushing component (8) is connected to the power component (6). A pressing unit (62) is connected to the box body (3), and the pressing unit (62) is also connected to the frame body (1). When the power component (6) is stationary, it is in transmission connection with the pressing unit (62). When the power component (6) is in motion, it is in transmission connection with the transmission component (7). The four-way pushing component (8) includes a first driving plate (803) and a second driving plate (805). The first driving plate (803) is symmetrically and slidably connected to the bottom wall of the circular box (9). The second driving plate (805) is symmetrically and slidably connected to the bottom wall of the circular box (9). A rotating disk (801) is coaxially and rotatably connected to the inner top wall of the circular box (9). A pushing column (802) is eccentrically and fixedly connected to the bottom wall of the rotating disk (801). During the rotation of the pushing column (802), it contacts the first driving plate (803) and the second driving plate (805) in sequence. The transmission component (7) includes a transmission shaft (701). The top end of the transmission shaft (701) is rotatably connected to the inner top wall of the box body (3). The other end of the transmission shaft (701) rotatably penetrates the bottom wall of the box body (3) and the top wall of the circular box (9) and is coaxially and fixedly connected to the rotating disk (801). And the extending end of the transmission shaft (701) is in frictional connection with the top wall of the circular box (9). The pneumatic fixing component (4) includes an I-shaped frame (401) and a vacuum box (403). The bottom wall of the vacuum box (403) is fixedly connected to the inner bottom wall of the frame body (1). The bottom of the I-shaped frame (401) is longitudinally slidably connected to the inner side wall of the vacuum box (403). The middle part of the I-shaped frame (401) is longitudinally slidably connected to the frame body (1). The upper part of the I-shaped frame (401) is located above the frame body (1). On both sides of the top wall of the upper part of the I-shaped frame (401), pneumatic push rods (405) are symmetrically and fixedly arranged. And the output ends of the symmetrically arranged pneumatic push rods (405) are arranged oppositely. The output end of the pneumatic push rod (405) is fixedly connected to a fixing plate (406). The base end of the pneumatic push rod (405) is communicated with the side wall of the vacuum box (403) through a pipeline.

2. The strength detection device for the landing bracket of an unmanned aerial vehicle according to claim 1, characterized in that: A first pushing plate (804) is fixedly connected to the first driving plate (803). A second pushing plate (806) is fixedly connected to the second driving plate (805). The first pushing plate (804) and the second pushing plate (806) penetrate the bottom wall of the circular box (9).

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