Four-rotor unmanned aerial vehicle impact vibration test tool

Abstract

The utility model discloses a quad-rotor unmanned aerial vehicle impact vibration test tool which comprises a fixing plate, the upper end of the fixing plate is provided with four lifting supporting feet which are symmetrically arranged in pairs, a top cover is arranged above the lifting supporting feet, and the top cover and the lifting supporting feet can form a clamping structure to clamp a fuselage arm of a quad-rotor unmanned aerial vehicle. The four-rotor unmanned aerial vehicle impact vibration test tool can effectively solve the problems that a traditional impact vibration test tool is heavy and complex to assemble and disassemble, the impact vibration test difficulty is reduced due to the characteristics of being light and easy to assemble, the four-rotor unmanned aerial vehicle impact vibration test tool can effectively simulate the suspension posture of an unmanned aerial vehicle in the flight process, and the test efficiency is improved. The accuracy of an impact vibration test result is effectively improved; the tool structure does not interfere with the movable part of the unmanned aerial vehicle, the unmanned aerial vehicle can be directly installed on the tool for debugging, and the four-rotor unmanned aerial vehicle impact vibration test tool is simple in structure and low in manufacturing cost and has good economic benefits.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to an impact vibration test tooling for a quad-rotor unmanned aerial vehicle. Background Art

[0002] Drones are easy to carry, simple to operate and use, and can be used in typical environments. They are gaining more and more attention in the military, industry and social life. In order for drones to meet military standards, a variety of environmental experiments and working condition tests are required during the development process. Among them, impact vibration tests are an effective measure to verify the structural strength of drones.

[0003] The impact vibration tooling for quad-rotor UAVs should be able to effectively lock and fix the UAV, and ensure that the vibration provided by the impact vibration test bench can be transmitted to the body, and the tooling cannot resonate with the UAV. To achieve this goal, conventional impact vibration tooling is often designed as a large-volume encapsulated tooling, which is bulky and difficult to disassemble and assemble. In order to solve this problem, this tooling is specially designed. Utility Model Content

[0004] In order to overcome the deficiencies of the prior art, the purpose of the present invention is to provide a quad-rotor UAV impact vibration test tooling to solve the technical problems mentioned in the background technology.

[0005] In order to solve the technical problem, the utility model adopts the following technical solution:

[0006] A quad-rotor unmanned aerial vehicle impact vibration test tool comprises a fixing plate, wherein the upper end of the fixing plate is provided with four raising legs which are symmetrically arranged in pairs, and a top cover is provided above the raising legs, wherein the top cover can form a clamping structure with the raising legs to clamp the fuselage arm of the quad-rotor unmanned aerial vehicle.

[0007] A further improvement is that a claw is provided at the upper end of the lifting leg, a claw groove is formed on the claw, a cover arm is provided at the lower end of the top cover, a cover arm groove is formed on the cover arm at a position corresponding to the claw groove, the claw groove and the cover arm groove are combined to form an arm fixing hole for clamping the fuselage arm of the quadrotor drone, and also includes side clamps, which are movably installed on both sides of the cover arm and the claw to fix the top cover and the lifting leg, wherein the claw, claw groove, cover arm, cover arm groove and the side clamps on both sides together constitute a clamping structure to clamp the fuselage arm.

[0008] A further improvement is that a cover arm screw hole is provided on the side of the cover arm, a claw screw hole is provided on the side of the claw, and a clamping plate through hole is provided at the position corresponding to the cover arm through hole and the claw through hole on the side clamping plate, and bolts pass through the above-mentioned through holes to fix the side clamping plate to the cover seat.

[0009] A further improvement is that an external supporting claw is provided on the outer side of the clamping claw, and a supporting claw groove is provided on the external supporting claw at a position coaxial with the clamping claw groove. The front end of the fuselage arm of the quadrotor drone is clamped by the arm through hole and the rear end is supported by the supporting claw groove to increase the test stability of the fuselage arm and reduce vibration.

[0010] A further improvement is that the lifting leg is divided into an upper supporting part and a bottom connecting part, the bottom connecting part is vertically arranged with the fixing plate, and the upper supporting part extends obliquely toward the top cover for support, a fixing seat is provided at the upper end of the fixing plate, and a connecting groove matching the shape of the bottom connecting part of the lifting leg is provided on the fixing seat, an outer slot hole is provided on the side of the connecting groove, and an inner slot hole is provided at a position of the bottom connecting part corresponding to the outer slot hole, and bolts are inserted from the side into the outer slot hole and the inner slot hole to realize the fixed connection between the lifting leg and the fixing seat, fixing ears are also provided on both sides of the fixing seat, and ear fixing holes are provided on the fixing ears, and plate fixing holes are provided at positions corresponding to the ear fixing holes on the fixing plate, and bolts pass through the ear fixing holes and the plate fixing holes to fix the fixing seat and the fixing plate.

[0011] A further improvement is that side holes are provided at the inner and outer edges of the fixing seat to increase the fixing force at the inner and outer sides of the fixing seat.

[0012] A further improvement is that the height of the raised support legs is higher than the height of the landing gear of the quad-rotor drone.

[0013] A further improvement is that the side clamping plate is L-shaped, with the upper end connected to the cover arm and the lower end connected to the clamping claw and the outer claw.

[0014] A further improvement is that the top cover is hollowed out to form a fuselage embedding hole. During the test, the upper end of the fuselage of the quad-rotor drone protrudes and embeds into the fuselage embedding hole.

[0015] Compared with the prior art, the beneficial effects of the present invention are:

[0016] (1) The quadcopter UAV impact vibration test tooling can effectively solve the problems of heavy weight and complicated loading and unloading of traditional impact vibration test tooling. Its light weight and easy assembly reduce the difficulty of impact vibration testing.

[0017] (2) The impact vibration test fixture of the quadcopter UAV can effectively simulate the suspended posture of the UAV during flight, effectively improving the accuracy of the impact vibration test results; the fixture structure does not interfere with the movable parts of the UAV, and the UAV can be directly installed on the fixture for debugging.

[0018] (3) The quad-rotor UAV impact vibration test tooling has a simple structure, low manufacturing cost, and good economic benefits. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 : This is a schematic diagram of the overall structure of the impact vibration test tooling for unmanned aerial vehicles of the utility model;

[0020] Figure 2 : This is a schematic diagram of the overall structure of the impact vibration test tooling for unmanned aerial vehicles of the utility model;

[0021] Figure 3 : It is a three-dimensional angle diagram of the lifting foot support structure of the utility model;

[0022] Figure 4 : It is a schematic diagram of the utility model's lifting foot support structure from a front view angle;

[0023] Figure 5 : It is a schematic diagram of the top cover structure of the utility model;

[0024] Figure 6 : It is a schematic diagram of the structure of the fixing seat of the utility model;

[0025] In the figure: fixing plate 1, lifting foot 2, top cover 3, claw 4, claw groove 5, cover arm 6, cover arm groove 7, side clamping plate 8, cover arm screw hole 9, claw screw hole 10, clamping plate through hole 11, outer claw 12, claw groove 13, upper support part 210, bottom connecting part 220, fixing seat 14, connecting groove 15, outer slot hole 16, inner slot hole 17, fixing ear 18, ear fixing hole 180, plate fixing hole 100, fuselage embedding hole 300, side hole 140. DETAILED DESCRIPTION

[0026] The present invention is further described below in conjunction with the accompanying drawings and specific implementation methods. It should be noted that, under the premise of no conflict, the various embodiments or technical features described below can be arbitrarily combined to form a new embodiment.

[0027] refer to Figures 1 to 6 :

[0028] Embodiment 1: The utility model patent discloses a quad-rotor UAV impact vibration test tooling, comprising a fixing plate 1, wherein the upper end of the fixing plate 1 is provided with four lifting legs 2 which are symmetrically arranged in pairs, and a top cover 3 is provided above the lifting legs 2, and the top cover 3 can form a clamping structure with the lifting legs 2 to clamp the fuselage arm of the quad-rotor UAV.

[0029] Specifically, a claw 4 is provided at the upper end of the lifting leg 2, and the claw 4 is located above the top end surface of the lifting leg 2 and is vertically arranged with the end surface thereof. A claw groove 5 is formed on the claw 4, and the claw groove 5 opens upward. A cover arm 6 is provided at the lower end of the top cover 3, and a cover arm groove 7 is formed on the cover arm 6 at a position corresponding to the claw groove 5, and the cover arm groove 7 opens downward. The claw groove 5 and the cover arm groove 7 enclose an arm fixing hole for clamping the fuselage arm of the quadcopter, and also include a side clamping plate 8, which is movably installed on both sides of the cover arm 6 and the claw 4 to fix the top cover 3 and the lifting leg 2, wherein the claw 4, claw groove 5, cover arm 6, cover arm groove 7 and the side clamping plates 8 on both sides together constitute a clamping structure to clamp the fuselage arm.

[0030] Specifically, the side of the cover arm 6 is provided with a cover arm screw hole, the side of the claw 4 is provided with a claw screw hole 10, and the side clamping plate 8 is provided with a clamping plate through hole 11 at the position corresponding to the through hole of the cover arm 6 and the through hole of the claw 4. The bolts pass through the above holes to fix the side clamping plate 8 to the cover base. Here, the cover arm screw hole and the claw screw hole 10 are both internal threaded holes, which are convenient for screwing in and fixing from the outside. When not in use, they can be directly loosened, the side clamping plate 8 can be removed, and then the top cover 3 is separated from the lifting support foot 2.

[0031] Specifically, an outer side of the clamping claw 4 is also provided with an outer claw 12, and the outer claw 12 is extended outward from the clamping claw 4. Specifically, the plane formed by the outer claw 12 and the clamping claw 4 is parallel to the fixed plate 1, so that the top cover 3 is clamped from the upper end to the bottom, and the four clamping claws 4 are aligned with the four cover arms 6 and clamped. After clamping, they are clamped by the side clamping plates 8. In order to further reduce the vibration of the fuselage arm and increase the stability of the tooling during the test, a claw groove 13 is provided on the outer claw 12 at a position coaxial with the claw groove 5. The front end of the fuselage arm of the quadcopter is clamped by the arm through hole, and the rear end is supported by the claw groove 13 to increase the test stability of the fuselage arm and reduce vibration at the same time.

[0032] Specifically, the lifting foot 2 is divided into an upper supporting portion 210 and a bottom connecting portion 220, the bottom connecting portion 220 is arranged vertically with the fixing plate 1, and the upper supporting portion 210 extends obliquely toward the top cover 3 as a support and a transition of the claw 4 and other components. The upper end of the fixing plate 1 is provided with a fixing seat 14, and the fixing seat 14 is provided with a connecting groove 15 matching the shape of the bottom connecting portion 220 of the lifting foot 2, and the side of the connecting groove 15 is provided with an outer slot hole 16, and the position of the bottom connecting portion 220 corresponding to the outer slot hole 16 is provided There is an inner slot hole 17, and bolts are inserted from the side into the outer slot hole 16 and the inner slot hole 17 to achieve a fixed connection between the lifting leg 2 and the fixing base 14. The inner slot hole 17 can be set as an internal threaded hole. The fixing base 14 is also provided with fixing ears 18 on both sides, and the fixing ears 18 are provided with ear fixing holes 180. The fixing plate 1 is provided with a plate fixing hole 100 at a position corresponding to the ear fixing hole 180. The plate fixing hole 100 can be set as an internal threaded hole. The bolts pass through the ear fixing hole 180 and the plate fixing hole 100 to fix the fixing base 14 to the fixing plate 1.

[0033] Specifically, the height of the lifting support leg 2 is higher than the height of the landing gear of the quadcopter UAV, which is convenient for simulating the suspended posture of the aircraft during flight.

[0034] Specifically, the side clamping plate 8 is L-shaped, with an upper end connected to the cover arm 6 and a lower end connected to the clamping claw 4 and the outer claw 12 .

[0035] Specifically, side holes 140 are provided at the inner and outer edges of the fixing seat 14 to increase the fixing force on the inner and outer sides of the fixing seat 14, so that fixing holes are formed on the front, back, left and right sides, and the fixing seat 14 and the fixing plate 1 are very firmly connected together.

[0036] Specifically, the top cover 3 is hollowed out to form a fuselage embedding hole 300, which matches the shape of the upper fuselage of the quad-rotor drone. During the test, the upper fuselage of the quad-rotor drone protrudes and embeds into the fuselage embedding hole 300, thereby providing stable wrapping for the fuselage of the drone.

[0037] The test principle of this test fixture is: use the clamping structure formed by the top cover 3 and the raised support foot 2 to fix the fuselage arm of the quadrotor drone, and use the neatly arranged screw holes on the fixing plate 1 to fix the fixture and the drone as a whole on the shock and vibration test bench. The shock and vibration test bench applies shock or vibration to observe the degree of system damage of the drone after shock and vibration. Because this fixture has a complete and symmetrical support structure and a stable clamping structure, it can effectively reduce the vibration caused by the structure during the test and increase the success rate of the test.

[0038] The above-mentioned implementation modes are only preferred implementation modes of the present invention, and cannot be used to limit the protection scope of the present invention. Any non-substantial changes and substitutions made by technicians in this field on the basis of the present invention shall fall within the scope of protection required by the present invention.

Claims

1. A quad-rotor UAV impact vibration test fixture, comprising a fixing plate, characterized in that: The upper end of the fixing plate is provided with four lifting legs which are symmetrically arranged in pairs, and a top cover is provided above the lifting legs, and the top cover can form a clamping structure with the lifting legs to clamp the fuselage arm of the quadrotor UAV; the upper end of the lifting legs is provided with a claw, and a claw groove is formed on the claw, and the lower end of the top cover is provided with a cover arm, and a cover arm groove is formed on the cover arm at a position corresponding to the claw groove, and the claw groove and the cover arm groove are combined to form an arm fixing hole for clamping the fuselage arm of the quadrotor UAV, and also include side clamps, which are movably installed on both sides of the cover arm and the claw to fix the top cover and the lifting legs, wherein the claw, claw groove, cover arm, cover arm groove and the side clamps on both sides together constitute a clamping structure to clamp the fuselage arm.

2. A quad-rotor UAV impact vibration test tool as claimed in claim 1, characterized in that: The side of the cover arm is provided with a cover arm screw hole, the side of the claw is provided with a claw screw hole, and the side clamping plate is provided with clamping plate through holes at positions corresponding to the cover arm through holes and the claw through holes. Bolts pass through the above through holes to fix the side clamping plate to the cover seat.

3. A quad-rotor UAV impact vibration test tool as described in any one of claims 1-2, characterized in that: An outer supporting claw is also provided on the outer side of the clamping claw, and a supporting claw groove is provided on the outer supporting claw at a position coaxial with the clamping claw groove. The front end of the fuselage arm of the quad-rotor drone is clamped by the arm through hole, and the rear end is supported by the supporting claw groove to increase the test stability of the fuselage arm and reduce vibration.

4. The quad-rotor UAV impact vibration test tooling as claimed in claim 1, characterized in that: The lifting foot is divided into an upper supporting part and a bottom connecting part, the bottom connecting part is vertically arranged with the fixing plate, and the upper supporting part extends obliquely toward the top cover for support, a fixing seat is provided at the upper end of the fixing plate, and a connecting groove matching the shape of the bottom connecting part of the lifting foot is provided on the fixing seat, an outer slot hole is provided on the side of the connecting groove, and an inner slot hole is provided at a position of the bottom connecting part corresponding to the outer slot hole, and bolts are inserted from the side into the outer slot hole and the inner slot hole to realize the fixed connection between the lifting foot and the fixing seat, fixing ears are also provided on both sides of the fixing seat, and ear fixing holes are provided on the fixing ears, and plate fixing holes are provided at positions corresponding to the ear fixing holes on the fixing plate, and bolts pass through the ear fixing holes and the plate fixing holes to fix the fixing seat and the fixing plate.

5. The quad-rotor UAV impact vibration test tool as claimed in claim 4, characterized in that: Side holes are also provided at the inner and outer edges of the fixing seat to increase the fixing force at the inner and outer edges of the fixing seat.

6. A quad-rotor UAV impact vibration test tool as claimed in claim 5, characterized in that: The height of the raised support legs is higher than the height of the landing gear of the quad-rotor drone.

7. The quad-rotor UAV impact vibration test tool as claimed in claim 3, characterized in that: The side clamping plate is L-shaped, the upper end of which is connected to the cover arm, and the lower end of which is connected to the clamping claw and the outer supporting claw.

8. The quad-rotor UAV impact vibration test tool as claimed in claim 3, characterized in that: The top cover is hollowed out to form a fuselage embedding hole. During the test, the upper end of the fuselage of the quad-rotor drone protrudes and embeds into the fuselage embedding hole.

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