Elastic adjustable unmanned aerial vehicle undercarriage

Abstract

The elasticity-adjustable unmanned aerial vehicle undercarriage comprises a vehicle body and a flying wing, the flying wing is arranged at the top of the vehicle body, and support assemblies are arranged on the two side faces of the vehicle body; each support assembly comprises two supporting rod pieces and two buffering assemblies, and one ends of the two supporting rod pieces are fixed to one side face of the machine body. The support assembly, the adjusting screw rod and the adjusting nut are arranged, the support assembly buffers landing of the unmanned aerial vehicle, the adjusting nut is rotated to drive the adjusting screw rod to move, the adjusting screw rod moves to drive the landing cross rod to move, the landing cross rod moves to extrude the spring piece, and the spring piece stretches out and draws back to change the elastic force of the spring piece. And the spring piece stops rotating after contracting to a proper position, so that the elastic force of the spring piece can be kept, and the effect of adjusting the elastic force of the spring piece on the bracket assembly is achieved.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle landing gear with adjustable elasticity. Background Art

[0002] An unmanned aerial vehicle is an unpiloted aircraft that flies through remote control or pre-programmed instructions. Currently, unmanned aerial vehicles are used in civilian and military fields. In the civilian field, they are used for photography, logistics distribution, search and rescue, and scientific research. Moreover, unmanned aerial vehicles are also divided into small, medium, and large types, and appropriate unmanned aerial vehicles are selected for use according to actual situations.

[0003] Since the unmanned aerial vehicle needs to land after takeoff, in order to avoid the impact on the unmanned aerial vehicle during landing, landing gears are provided at the bottom of the unmanned aerial vehicle. The landing gears buffer the impact generated during the landing of the unmanned aerial vehicle to protect the unmanned aerial vehicle. Since the landing areas of the unmanned aerial vehicle are also different, such as the impact generated when landing on sand and when landing on a cement floor is completely different, and the unmanned aerial vehicle itself carries payloads of different weights, the requirements for the buffering performance are also different. However, it is very difficult to adjust the elasticity of the existing landing gears according to the actual usage situation, which affects the buffering performance of the landing gears.

[0004] Therefore, how to provide an unmanned aerial vehicle landing gear with adjustable elasticity is an urgent problem to be solved by those skilled in the art. Summary of the Utility Model

[0005] An object of the utility model is to provide an unmanned aerial vehicle landing gear with adjustable elasticity, and the utility model solves the problem that it is very difficult to adjust the elasticity of the existing unmanned aerial vehicle landing gear according to the actual usage situation, which affects the buffering performance of the landing gear.

[0006] An unmanned aerial vehicle landing gear with adjustable elasticity according to an embodiment of the utility model includes a fuselage and flight wings. The flight wings are arranged on the top of the fuselage, and support assemblies are arranged on both sides of the fuselage;

[0007] Each support assembly includes two support rods and two buffer assemblies. One ends of the two support rods are fixed on one side of the fuselage, and the other ends of the two support rods are fixed to the tops of the two buffer assemblies. The two buffer assemblies include a fixed cylinder, a buffer rod, and a spring member. The fixed cylinder is fixed at the end of the two support rods away from the fuselage. The buffer rod moves inside the fixed cylinder, and the other end of the buffer rod extends outside the fixed cylinder after passing through the fixed cylinder. The spring member is movably sleeved on the surface of the buffer rod outside the fixed cylinder. A landing cross bar is fixed at the end of the buffer rod away from the fixed cylinder. One end of the spring member moves on the surface of the fixed cylinder, and the other end of the spring member moves on the surface of the landing cross bar;

[0008] An adjusting screw is provided on the upper surface of the lifting cross bar. On the opposite surfaces of the two fixed cylinders in each bracket assembly, a fixed bar parallel to the lifting cross bar is provided. A through hole is provided on the fixed bar. One end of the adjusting screw passes through the through hole and extends to the other side of the through hole. An adjusting nut is threadedly sleeved on the surface of the adjusting screw on the side of the fixed bar away from the lifting cross bar. One side of the adjusting nut is movably connected to the surface of the fixed bar.

[0009] The support member includes an inclined cylinder and an adjusting plate. One end of the inclined cylinder is fixed to the side surface of the fuselage. One end of the adjusting plate is fixed to the end surface of the fixed cylinder. The other end of the adjusting plate is movably inside the inclined cylinder. A fixing bolt is provided at a position on the upper surface of the inclined cylinder away from the fuselage. The bottom end of the fixing bolt passes through the inclined cylinder and fits on the surface of the adjusting plate.

[0010] A scale is provided on the surface of the adjusting plate.

[0011] The adjusting screw is fixed on the axis of symmetry of the lifting cross bar and is perpendicular to the lifting cross bar. The entire buffer assembly is vertically arranged.

[0012] A strip-shaped air bag is provided on the lower surface of the lifting cross bar.

[0013] The beneficial effects of the present utility model are as follows:

[0014] By providing the bracket assembly, the adjusting screw and the adjusting nut, the bracket assembly buffers the landing of the drone. Then, for different usage environments, by rotating the adjusting nut to drive the adjusting screw to move, the adjusting screw drives the lifting cross bar to move. The movement of the lifting cross bar will squeeze the spring member, causing the spring member to expand and contract to change the elastic force of the spring member. After the spring member contracts to a suitable position, stop rotating. In this way, the elastic force of the spring member can be maintained, achieving the effect of adjusting the elastic force of the spring member on the bracket assembly, and solving the problem that the elastic force of the existing drone landing gear is difficult to adjust according to the actual usage situation, which affects the buffering performance of the landing gear. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The drawings are used to provide a further understanding of the present utility model and constitute a part of the specification. Together with the embodiments of the present utility model, they are used to explain the present utility model and do not constitute a limitation to the present utility model. In the drawings:

[0016] Figure 1 It is an overall three-dimensional flow chart of an elastic adjustable drone landing gear proposed by the present utility model.

[0017] Figure 2 It is a cross-sectional three-dimensional flow chart of the support member and the buffer assembly in an elastic adjustable drone landing gear proposed by the present utility model.

[0018] Figure 3A cross-sectional three-dimensional flowchart for adjusting the position of the adjusting screw in an elastically adjustable landing gear of a drone proposed by the present utility model.

[0019] Reference numerals in the attached drawings: 1, airframe; 2, flight wing; 3, bracket assembly; 4, support rod member; 5, buffer assembly; 6, fixed cylinder; 7, buffer rod; 8, spring member; 9, landing cross bar; 10, adjusting screw; 11, fixed rod; 12, through hole; 13, adjusting nut; 14, inclined cylinder; 15, adjusting plate; 16, fixing bolt; 17, scale; 18, strip-shaped inflatable airbag. Detailed implementation manners

[0020] Now, the present utility model will be further described in detail with reference to the accompanying drawings. These drawings are all simplified schematic diagrams, only illustrating the basic structure of the present utility model in a schematic manner, so they only show the components related to the present utility model.

[0021] Embodiment 1

[0022] Refer to Figure 1 , including an airframe 1 and a flight wing 2, the flight wing 2 is arranged on the top of the airframe 1, bracket assemblies 3 are arranged on both side surfaces of the airframe 1, and the bracket assemblies 3 are landing gear members for buffering the landing of the drone;

[0023] Refer to Figure 1 and Figure 2 , each group of the bracket assemblies 3 includes two groups of support rod members 4 and two groups of buffer assemblies 5. One ends of the two groups of support rod members 4 are fixed on one side surface of the airframe 1, and the other ends of the two groups of support rod members 4 are fixed to the tops of the two groups of buffer assemblies 5. The two groups of buffer assemblies 5 include a fixed cylinder 6, a buffer rod 7 and a spring member 8. The fixed cylinder 6 is fixed at the end of the two groups of support rod members 4 away from the airframe 1. The buffer rod 7 moves inside the fixed cylinder 6, and the end of the buffer rod 7 that moves with the fixed cylinder 6 is a damping end, so as to achieve a damping effect. The other end of the buffer rod 7 extends outside the fixed cylinder 6 after passing through the fixed cylinder 6. The spring member 8 is movably sleeved on the surface of the buffer rod 7 outside the fixed cylinder 6. The end of the buffer rod 7 away from the fixed cylinder 6 is fixed with a landing cross bar 9. A strip-shaped inflatable airbag 18 is arranged on the lower surface of the landing cross bar 9 for directly contacting the ground when the drone lands to perform the first-step buffering of the impact generated by the landing, and it is not easy to generate a rigid collision. One end of the spring member 8 moves on the surface of the fixed cylinder 6, and the other end of the spring member 8 moves on the surface of the landing cross bar 9. When the drone lands, the strip-shaped inflatable airbag 18 under the landing cross bar 9 performs the first-step buffering to avoid a rigid collision. Then, the impact will drive the buffer rod 7 to contract into the fixed cylinder 6 through the landing cross bar 9. When the buffer rod 7 contracts and buffers, the spring member 8 will be squeezed, so that the spring member 8 contracts to buffer, achieving the effect of buffering the landing of the drone;

[0024] Refer to Figure 3, an adjusting screw rod 10 is arranged on the upper surface of the lifting cross bar 9. The adjusting screw rod 10 is fixed on the axis of symmetry of the lifting cross bar 9 and is perpendicular to the lifting cross bar 9. The entire buffer assembly 5 is arranged vertically. On the opposite surfaces of the two fixed cylinders 6 in each bracket assembly 3, there is a fixed rod 11 parallel to the lifting cross bar 9. A through hole 12 is formed in the fixed rod 11. One end of the adjusting screw rod 10 passes through the through hole 12 and extends to the other side of the through hole 12. On the surface of the adjusting screw rod 10, on the side away from the lifting cross bar 9 of the fixed rod 11, an adjusting nut 13 is threadedly sleeved. One side of the adjusting nut 13 is movably connected to the surface of the fixed rod 11. The adjusting screw rod 10 is fixed on the axis of symmetry of the lifting cross bar 9 and is perpendicular to the lifting cross bar 9. The entire buffer assembly 5 is arranged vertically. In order to change the elastic force of the spring member 8, it is necessary to rotate the adjusting nut 13 to drive the adjusting screw rod 10 to move upward. When the adjusting screw rod 10 moves upward, it will drive the lifting cross bar 9 to move upward. When the lifting cross bar 9 moves up and down, it drives the buffer rod 7 to contract into the fixed cylinder 6 and at the same time squeezes the spring member 8. The spring member 8 contracts under the extrusion to change the elastic force, achieving the effect of adjusting the elastic force of the spring member 8.

[0025] Embodiment 2

[0026] Reference Figure 1 and Figure 2 , the support member 4 includes an inclined cylinder 14 and an adjusting plate 15. One end of the inclined cylinder 14 is fixed on the side surface of the machine body 1, and one end of the adjusting plate 15 is fixed on the end surface of the fixed cylinder 6. The other end of the adjusting plate 15 is movably inside the inclined cylinder 14. At a position on the upper surface of the inclined cylinder 14 away from the machine body 1, there is a fixing bolt 16. The bottom end of the fixing bolt 16 passes through the inclined cylinder 14 and fits on the surface of the adjusting plate 15. A scale 17 is arranged on the surface of the adjusting plate 15 for observing the adjusted position of the adjusting plate 15 to make it the same as the adjusted positions of other adjusting plates 15. During operation, loosen the fixing bolt 16, so that the adjusting plate 15 will move on the inclined cylinder 14, causing the adjusting plate 15 to extend outwards, which will drive the buffer assembly 5 to move away from the machine body 1. In this way, the buffer assembly 5 can be moved outwards to increase the support range of the entire bracket assembly 3. If the adjusting plate 15 is contracted inwards, the support range of the entire bracket assembly 3 will be reduced. When the adjusting plate 15 is adjusted to the appropriate position, reverse-rotate the fixing bolt 16 to fix the adjusting plate 15 inside the inclined cylinder 14, achieving the effect of adjusting the support range of the bracket assembly 3.

[0027] The above is only a preferred specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention, according to the technical solution of the present invention and its inventive concept, makes equivalent substitutions or changes, and all should be covered within the protection scope of the present invention.

Claims

1. An elastically adjustable landing gear for a drone, characterized in that, It includes a body (1) and a flight wing (2). The flight wing (2) is arranged on the top of the body (1), and support assemblies (3) are arranged on both side surfaces of the body (1); Each of the support assemblies (3) includes two support rods (4) and two buffer assemblies (5). One ends of the two support rods (4) are fixed to one side surface of the body (1), and the other ends of the two support rods (4) are fixed to the tops of the two buffer assemblies (5). Each of the two buffer assemblies (5) includes a fixed cylinder (6), a buffer rod (7), and a spring member (8). The fixed cylinder (6) is fixed to the end of the two support rods (4) away from the body (1). The buffer rod (7) is movably arranged inside the fixed cylinder (6). The other end of the buffer rod (7) extends outside the fixed cylinder (6) after passing through the fixed cylinder (6). The end of the buffer rod (7) movably connected to the fixed cylinder (6) is a damping end. The spring member (8) is movably sleeved on the surface of the buffer rod (7) outside the fixed cylinder (6). A landing cross bar (9) is fixed to the end of the buffer rod (7) away from the fixed cylinder (6). One end of the spring member (8) is movably arranged on the surface of the fixed cylinder (6), and the other end of the spring member (8) is movably arranged on the surface of the landing cross bar (9); An adjusting screw (10) is arranged on the upper surface of the landing cross bar (9). Fixed rods (11) parallel to the landing cross bar (9) are arranged on the opposite surfaces of the two fixed cylinders (6) in each support assembly (3). Through holes (12) are formed in the fixed rods (11). One end of the adjusting screw (10) extends to the other side of the through hole (12) after passing through the through hole (12). An adjusting nut (13) is threadedly sleeved on the surface of the adjusting screw (10) on the side of the fixed rod (11) away from the landing cross bar (9). One side of the adjusting nut (13) is movably connected to the surface of the fixed rod (11).

2. An elastic adjustable drone landing gear according to claim 1, characterized in that, Each of the support rods (4) includes an inclined cylinder (14) and an adjusting plate (15). One end of the inclined cylinder (14) is fixed to the side surface of the body (1). One end of the adjusting plate (15) is fixed to the end face of the fixed cylinder (6). The other end of the adjusting plate (15) is movably arranged inside the inclined cylinder (14). A fixing bolt (16) is arranged at a position on the upper surface of the inclined cylinder (14) away from the body (1). The bottom end of the fixing bolt (16) passes through the inclined cylinder (14) and abuts against the surface of the adjusting plate (15).

3. The elastic adjustable drone landing gear according to claim 2, characterized in that, A scale (17) is arranged on the surface of the adjusting plate (15).

4. The elastic adjustable drone landing gear according to claim 3, characterized in that, The adjusting screw (10) is fixed on the axis of symmetry of the landing cross bar (9) and is perpendicular to the landing cross bar (9), and the entire buffer assembly (5) is arranged vertically.

5. An elastic adjustable drone landing gear according to claim 4, characterized in that, A strip-shaped air bag (18) is arranged on the lower surface of the landing cross bar (9).

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