Device for testing flight attitude of unmanned aerial vehicle

Abstract

The utility model discloses an unmanned aerial vehicle flight attitude testing device, which comprises an unmanned aerial vehicle and a tester body, the top end of the unmanned aerial vehicle is fixedly connected with a mounting seat, a mounting block is inserted in the mounting seat, the mounting block is fixedly connected to the bottom end of the tester body, two sides of the inner wall of the mounting seat are both provided with accommodating cavities, and the accommodating cavities are communicated with the tester body. Connecting grooves are formed in the two ends of one side of the inner wall of the containing cavity, reset springs are fixedly connected to the inner walls of the two connecting grooves, a displacement plate is fixedly connected to one ends of the two reset springs, a plurality of limiting rods are fixedly connected to the surface of the displacement plate, an iron sheet is fixedly embedded in the middle of the displacement plate, and connecting cylinders are fixedly embedded in the four corners of the tester body; according to the flight attitude testing device for the unmanned aerial vehicle, the tester body is convenient to disassemble and assemble on the unmanned aerial vehicle, the working efficiency of flight attitude testing of the unmanned aerial vehicle is improved, a buffer protection structure is arranged, and the tester body is prevented from being damaged due to careless falling when the tester body is carried or disassembled on the unmanned aerial vehicle.

Description

Technical Field

[0001] The utility model relates to the technical field of testing devices, in particular to a flight attitude testing device for unmanned aerial vehicles. Background Art

[0002] Unmanned aerial vehicle, also known as "UAV", is an unmanned aircraft that is controlled by radio remote control equipment and its own program control device.

[0003] Drones require test equipment to evaluate, test and verify drone performance, flight characteristics and system functions, but existing drone test equipment has the following shortcomings:

[0004] (1) The existing UAV test equipment is difficult to disassemble and assemble on the UAV, and often requires the use of tools, resulting in low efficiency of UAV flight attitude testing;

[0005] (2) Existing UAV test devices lack a better protective structure. When being carried or disassembled on the UAV, the test device may be easily damaged if it falls accidentally. Utility Model Content

[0006] The purpose of the utility model is to provide a UAV flight attitude test device to solve the problem that the existing UAV test device proposed in the above background technology is troublesome to disassemble and assemble on the UAV, and tools are often needed, resulting in low efficiency of UAV flight attitude testing. The UAV test device lacks a better protective structure, and when being carried or disassembled on the UAV, it is easy to cause damage to the test device if it accidentally falls.

[0007] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a UAV flight attitude testing device, comprising a UAV and a tester body, the top of the UAV is fixedly connected with a mounting seat, the interior of the mounting seat is plugged with a mounting block, and the mounting block is fixedly connected to the bottom end of the tester body, both sides of the inner wall of the mounting seat are provided with accommodating cavities, both ends of one side of the inner wall of the accommodating cavity are provided with connecting grooves, the inner walls of the two connecting grooves are fixedly connected with reset springs, one end of the two reset springs is fixedly connected with a displacement plate, the surface of the displacement plate is fixedly connected with a plurality of limit rods, the middle part of the displacement plate is fixedly embedded with an iron sheet, the four corners of the tester body are fixedly embedded with connecting tubes, one end of the connecting tube is inserted with a support rod, one end of the support rod is fixedly connected with a guard plate, and a spring piece is placed on the inner wall of the connecting tube.

[0008] When the UAV flight attitude test device of the present technical solution is used, the tester body can be easily assembled and disassembled on the UAV, thereby improving the work efficiency of the UAV flight attitude test. The tester body has a buffer protection structure to prevent the tester body from being accidentally dropped and damaged when being carried or assembled and disassembled on the UAV.

[0009] As a preferred technical solution of the utility model, a plurality of limit slots are provided on both sides of the mounting block, and one end of the limit rod is inserted into the inner wall of the limit slot. The end of the limit rod is inserted into the limit slot to lock the position of the mounting block and the tester body.

[0010] As a preferred technical solution of the utility model, an electromagnet is fixedly embedded in the middle of one side of the inner wall of the accommodating cavity, and the electromagnet can overcome the elastic force of the spring to adsorb the iron sheet.

[0011] As a preferred technical solution of the utility model, a shifting block is fixedly connected to the top of the displacement plate, and a displacement opening is provided at the top of the inner wall of the accommodating cavity. The displacement plate can be driven to move by shifting the shifting block.

[0012] As a preferred technical solution of the utility model, the shift block is slidably connected to the inner wall of the displacement port, and the displacement port provides space for the movement of the shift block.

[0013] As a preferred technical solution of the utility model, both ends of the four sides of the tester body are fixedly embedded with connection seats, the inner wall of the connection seat is fixedly connected with a slide bar, one side of the slide bar surface is sleeved with a slide sleeve, the other side of the slide bar surface is sleeved with a buffer spring, the surface of the slide sleeve is rotatably connected with a connecting rod, and one end of the connecting rod is rotatably connected with one side of the inner wall of the guard plate. The provided connecting rod plays a role of transmission.

[0014] As a preferred technical solution of the utility model, one end of the buffer spring is fixedly connected to the sliding sleeve, and the other end of the buffer spring is fixedly connected to the inner wall of the connecting seat. Fixing the two ends of the buffer spring can prevent it from shifting or falling off on the sliding rod.

[0015] As a preferred technical solution of the utility model, one end of the spring piece is fixedly connected to the inner wall of the connecting tube, and the other end of the spring piece is fixedly connected to the support rod. Fixing the two ends of the spring piece can prevent it from shaking in the connecting tube.

[0016] Compared with the prior art, the beneficial effects of the utility model are:

[0017] 1. Fix the mounting base of the test device on the top surface of the drone, and disengage or insert the limit rod into the limit groove by switching the electromagnet or manually turning the dial block, so that the tester body can be disassembled and assembled. Therefore, the tester body is easy to disassemble and assemble on the drone, which improves the work efficiency of the drone flight attitude test;

[0018] 2. By setting guard plates at the four corners of the tester body, when it is hit accidentally, the guard plates will drive the support rod to move and squeeze the shrapnel, and drive the sliding sleeve to move and squeeze the buffer spring through the connecting rod. Then, under the action of the shrapnel and the elastic force of the buffer spring, the impact force can be better buffered, avoiding the tester body from being accidentally dropped and damaged when being carried or disassembled on a drone. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a structural schematic diagram of the utility model;

[0020] Figure 2 It is a three-dimensional diagram of the tester body of the utility model;

[0021] Figure 3 It is a cross-sectional view of the mounting seat of the utility model;

[0022] Figure 4 It is a cross-sectional view of the guard plate of the present invention.

[0023] In the figure: 1. UAV; 2. Mounting seat; 3. Mounting block; 4. Tester body; 5. Accommodating chamber; 6. Connecting groove; 7. Reset spring; 8. Displacement plate; 9. Limit rod; 10. Limit groove; 11. Iron sheet; 12. Electromagnet; 13. Shift block; 14. Displacement port; 15. Connecting tube; 16. Shrapnel; 17. Support rod; 18. Guard plate; 19. Connecting seat; 20. Slide rod; 21. Slide sleeve; 22. Connecting rod; 23. Buffer spring. DETAILED DESCRIPTION

[0024] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0025] See also Figure 1-4The utility model provides a UAV flight attitude test device, including a UAV 1 and a tester body 4, the top of the UAV 1 is fixedly connected with a mounting seat 2, the interior of the mounting seat 2 is plugged with a mounting block 3, and the mounting block 3 is fixedly connected to the bottom end of the tester body 4 for testing the flight attitude of the UAV 1, both sides of the inner wall of the mounting seat 2 are provided with accommodating chambers 5, both ends of one side of the inner wall of the accommodating chamber 5 are provided with connecting grooves 6, the inner walls of the two connecting grooves 6 are fixedly connected with reset springs 7, one end of the two reset springs 7 is fixedly connected with a displacement plate 8, the surface of the displacement plate 8 is fixedly connected with a plurality of limit rods 9 for disassembly and assembly of the tester body 4, the middle part of the displacement plate 8 is fixedly embedded with an iron sheet 11, the four corners of the tester body 4 are fixedly embedded with connecting tubes 15, one end of the connecting tube 15 is inserted and connected with a support rod 17, one end of the support rod 17 is fixedly connected with a guard plate 18, and the inner wall of the connecting tube 15 is provided with a spring sheet 16 for buffering and protection.

[0026] When in use, the mounting base 2 of the test device is fixed on the top surface of the drone 1, so that the tester body 4 follows the drone 1 to evaluate, test and verify the performance, flight attitude and system functions of the drone 1. The tester body 4 is easy to disassemble and assemble on the drone 1, which improves the work efficiency of the flight attitude test of the drone 1. A buffer protection structure is also provided to prevent the tester body 4 from being accidentally dropped and damaged when being carried or disassembled and assembled on the drone 1.

[0027] A plurality of limit grooves 10 are provided on both sides of the mounting block 3, and one end of the limit rod 9 is inserted into the inner wall of the limit groove 10 to play a locking role. An electromagnet 12 is fixedly embedded in the middle of one side of the inner wall of the accommodating chamber 5, which can adsorb the iron sheet 11. A shift block 13 is fixedly connected to the top of the displacement plate 8, and a displacement opening 14 is provided at the top of the inner wall of the accommodating chamber 5. The shift block 13 is slidably connected to the inner wall of the displacement opening 14 to provide moving space.

[0028] When in use, the iron sheet 11 on the displacement plate 8 is adsorbed by starting the electromagnet 12, so that the limit rod 9 is disengaged from the limit groove 10, thereby releasing the lock and allowing the mounting block 3 and the tester body 4 to be removed. The limit rod 9 can also be manually moved by toggling the shift block 13. After turning off the electromagnet 12 or releasing the shift block 13, the limit rod 9 will be reinserted into the limit groove 10 under the action of the reset spring 7 to lock the position of the tester body 4.

[0029] A connecting seat 19 is fixedly embedded at both ends of the four sides of the tester body 4, a sliding rod 20 is fixedly connected to the inner wall of the connecting seat 19, a sliding sleeve 21 is sleeved on one side of the surface of the sliding rod 20, and a buffer spring 23 is sleeved on the other side of the surface of the sliding rod 20 to further improve the buffering effect, a connecting rod 22 is rotatably connected to the surface of the sliding sleeve 21, and one end of the connecting rod 22 is rotatably connected to one side of the inner wall of the guard plate 18 to play a transmission role, one end of the buffer spring 23 is fixedly connected to the sliding sleeve 21, and the other end of the buffer spring 23 is fixedly connected to the inner wall of the connecting seat 19 to prevent displacement or falling off, one end of the spring 16 is fixedly connected to the inner wall of the connecting tube 15, and the other end of the spring 16 is fixedly connected to the support rod 17 to improve the installation stability.

[0030] When in use, by setting guard plates 18 at the four corners of the tester body 4, when it is accidentally hit, the guard plates 18 will drive the support rod 17 to move and squeeze the spring piece 16, and drive the sliding sleeve 21 to move and squeeze the buffer spring 23 through the connecting rod 22, and then under the action of the elastic force of the spring piece 16 and the buffer spring 23, it can play a better buffering role on the impact force and reduce the damage to the tester body 4.

[0031] When used specifically, the utility model unmanned aerial vehicle flight attitude test device fixes the mounting base 2 of the test device on the top surface of the unmanned aerial vehicle 1, so that the tester body 4 follows the flight of the unmanned aerial vehicle 1 to evaluate, test and verify the performance, flight attitude and system functions of the unmanned aerial vehicle 1, and the iron sheet 11 on the displacement plate 8 is adsorbed by starting the electromagnet 12, so that the limit rod 9 is disengaged from the inside of the limit groove 10, thereby releasing the lock and allowing the mounting block 3 and the tester body 4 to be removed, or the limit rod 9 can be manually moved by toggling the dial block 13, and after turning off the electromagnet 12 or releasing the dial block 13, the limit rod 9 will be under the action of the reset spring 7 Reinsert it into the limit slot 10 to lock the position of the tester body 4, so that the tester body 4 is easy to disassemble and assemble on the drone 1, which improves the work efficiency of the flight attitude test of the drone 1. By arranging guard plates 18 at the four corners of the tester body 4, when it is accidentally hit, the guard plate 18 will drive the support rod 17 to move and squeeze the spring piece 16, and drive the sliding sleeve 21 to move and squeeze the buffer spring 23 through the connecting rod 22, and then under the action of the elastic force of the spring piece 16 and the buffer spring 23, the impact force can be better buffered to avoid the tester body 4 from being accidentally dropped and damaged when being carried or disassembled on the drone 1.

[0032] Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art may still modify the technical solutions described in the aforementioned embodiments, or make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention shall be included in the protection scope of the present invention.

Claims

1. A UAV flight attitude test device, comprising a UAV (1) and a tester body (4), characterized in that: The top of the drone (1) is fixedly connected to a mounting seat (2), a mounting block (3) is inserted into the interior of the mounting seat (2), and the mounting block (3) is fixedly connected to the bottom of the tester body (4), both sides of the inner wall of the mounting seat (2) are provided with accommodating cavities (5), both ends of one side of the inner wall of the accommodating cavity (5) are provided with connecting grooves (6), the inner walls of the two connecting grooves (6) are fixedly connected to reset springs (7), one end of the two reset springs (7) is fixedly connected to a displacement plate (8), a plurality of limit rods (9) are fixedly connected to the surface of the displacement plate (8), an iron sheet (11) is fixedly embedded in the middle of the displacement plate (8), and the four corners of the tester body (4) are fixedly embedded with connecting tubes (15), one end of the connecting tube (15) is inserted and connected with a support rod (17), one end of the support rod (17) is fixedly connected to a guard plate (18), and a spring sheet (16) is placed on the inner wall of the connecting tube (15).

2. The UAV flight attitude test device according to claim 1, characterized in that: A plurality of limiting grooves (10) are provided on both sides of the mounting block (3), and one end of the limiting rod (9) is inserted into the inner wall of the limiting groove (10).

3. The UAV flight attitude test device according to claim 1, characterized in that: An electromagnet (12) is fixedly embedded in the middle of one side of the inner wall of the accommodating cavity (5).

4. The UAV flight attitude test device according to claim 1, characterized in that: A shift block (13) is fixedly connected to the top of the displacement plate (8), and a displacement opening (14) is provided at the top of the inner wall of the accommodating cavity (5).

5. The UAV flight attitude test device according to claim 4, characterized in that: The shifting block (13) is slidably connected to the inner wall of the displacement opening (14).

6. The UAV flight attitude test device according to claim 1, characterized in that: A connecting seat (19) is fixedly embedded at both ends of the four sides of the tester body (4); a sliding rod (20) is fixedly connected to the inner wall of the connecting seat (19); a sliding sleeve (21) is sleeved on one side of the surface of the sliding rod (20); a buffer spring (23) is sleeved on the other side of the surface of the sliding rod (20); a connecting rod (22) is rotatably connected to the surface of the sliding sleeve (21); and one end of the connecting rod (22) is rotatably connected to one side of the inner wall of the guard plate (18).

7. The UAV flight attitude test device according to claim 6, characterized in that: One end of the buffer spring (23) is fixedly connected to the sliding sleeve (21), and the other end of the buffer spring (23) is fixedly connected to the inner wall of the connecting seat (19).

8. The UAV flight attitude test device according to claim 1, characterized in that: One end of the spring sheet (16) is fixedly connected to the inner wall of the connecting tube (15), and the other end of the spring sheet (16) is fixedly connected to the support rod (17).

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