Unmanned aerial vehicle with landing buffer structure

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle with a landing buffer structure. According to the technical scheme, the unmanned aerial vehicle comprises a vehicle body and landing frames, a speed sensor and a controller are installed in the vehicle body, a parachute pack electrically connected with the controller is fixed to the upper end of the vehicle body, a parachute is arranged in the parachute pack, the landing frames are fixed to the bottom of the vehicle body and symmetrically distributed, the landing frames are of a U-shaped structure, and buffer rods are installed at the bottoms of the landing frames; a wear-resisting plate is installed at the bottom of the buffer rod on the same side, a dismounting assembly is arranged between the bottom of the buffer rod and the wear-resisting plate, and the upper end of the buffer rod is located in the landing frame and provided with a buffer assembly. On the basis that the parachute pack is opened and slowly descends, the buffering rod is used for landing buffering, it is guaranteed that the landing frame at the bottom lands, impact on a fuselage is reduced, meanwhile, the detachable wear-resisting plate is arranged at the bottom, and the replacement cost can be reduced after abrasion occurs.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles (UAVs), in particular to a UAV with a landing buffer structure. Background Art

[0002] A drone is an aircraft that does not require human operators. It can fly autonomously based on a preset flight path or be operated by remote control. Drones are widely used in military, civilian and commercial fields. Their uses include but are not limited to reconnaissance, surveillance, aerial photography, environmental monitoring, agricultural spraying, logistics distribution and disaster relief.

[0003] During the flight of a drone, if its power fan blades fail, the drone will fall directly from a high altitude, causing damage to the entire fuselage. A common protective structure is to set a parachute structure on the top of the aircraft. When the drone loses control and falls rapidly, the parachute in the parachute bag will automatically open to achieve the purpose of speed reduction buffering. However, during normal landing, the support frame is mainly used for buffering. During this process, if there is no buffering structure at the bottom of the support frame, it will cause excessive impact force on the fuselage, causing damage to the fuselage, and the bottom is in direct contact with the ground. Long-term use will also cause wear on the bottom. The support frame needs to be replaced during replacement, and the replacement cost is relatively high. Utility Model Content

[0004] The purpose of the present invention is to provide a UAV with a landing buffer structure to solve the problems raised in the above background technology.

[0005] To achieve the above-mentioned purpose, the present invention provides the following technical solution: it includes a fuselage and a landing gear, a speed sensor and a controller are installed in the fuselage, a parachute bag electrically connected to the controller is fixed to the upper end of the fuselage, a parachute is arranged in the parachute bag, the landing gear is fixed to the bottom of the fuselage and is symmetrically distributed, the landing gear is a U-shaped structure, and a buffer rod is installed at the bottom, a wear-resistant plate is installed at the bottom of the buffer rod on the same side, a disassembly and assembly component is arranged between the bottom of the buffer rod and the wear-resistant plate, the upper end of the buffer rod is located in the landing gear and is provided with a buffer component.

[0006] Preferably, the buffer assembly includes a cavity and a piston plate, the cavity is opened at the bottom of the landing gear and is aligned with the buffer rod, the piston plate is slidably connected in the cavity, the upper end of the buffer rod is located in the cavity and fixed on the piston plate.

[0007] Preferably, a return spring is fixed between the bottom of the piston plate and the bottom of the cavity, and a pressure relief hole is provided on the side wall of the upper end of the cavity.

[0008] Preferably, the disassembly and assembly component includes an elliptical plate and a card slot, a connecting block is fixed at the bottom of the buffer rod, the elliptical plate is rotatably connected to the bottom of the connecting block, an adaptation groove is provided at the upper end of the wear-resistant plate and aligned with the buffer rod, a card slot is provided at the bottom of the wear-resistant plate and corresponding to the adaptation groove, a connecting hole is provided between the card slot and the adaptation slot, the elliptical plate passes through the connecting hole and is clamped in the card slot.

[0009] Preferably, the connecting block and the elliptical plate are elliptical structures of the same size and the same size as the connecting hole, the adapting groove and the clamping groove are both circular structures and the same size as the buffer rod, and the diameter of the clamping groove is the same as the long diameter of the elliptical plate.

[0010] Preferably, a rotating shaft is provided between the elliptical plate and the connecting block, and a torsion spring is installed at the connection.

[0011] Compared with the existing technology, the beneficial effects of the present invention are: on the basis of opening the parachute pack and landing slowly, the buffer rod is used to cushion the landing, ensuring that the bottom landing gear touches the ground and reducing the impact on the fuselage. At the same time, a detachable wear-resistant plate is provided at the bottom, which can reduce the replacement cost after wear occurs. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 This is a front cross-sectional structural diagram of a UAV with a landing buffer structure according to the present invention;

[0013] Figure 2 This is a schematic diagram of the internal structure of a UAV landing frame with a landing buffer structure according to the present invention;

[0014] Figure 3 This utility model is a UAV with a landing buffer structure Figure 1 A in the middle is an enlarged structural diagram;

[0015] Figure 4 This is a schematic diagram of the cross-sectional structure of a wear-resistant plate of a UAV with a landing buffer structure according to the present invention.

[0016] In the figure: 1. Fuselage; 11. Parachute bag; 12. Parachute; 2. Landing gear; 21. Cavity; 22. Piston plate; 23. Pressure relief hole; 3. Buffer rod; 31. Connecting block; 32. Elliptical plate; 4. Wear-resistant plate; 41. Adapter groove; 42. Connecting hole; 43. Card slot. DETAILED DESCRIPTION

[0017] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0018] See also Figure 1-4 The utility model provides a technical solution: it includes a fuselage 1 and a landing gear 2, a speed sensor and a controller are installed in the fuselage 1, a parachute bag 11 electrically connected to the controller is fixed to the upper end of the fuselage 1, and a parachute 12 is arranged in the parachute bag 11, the landing gear 2 is fixed to the bottom of the fuselage 1 and is symmetrically distributed, the landing gear 2 is a U-shaped structure, and a buffer rod 3 is installed at the bottom, a wear-resistant plate 4 is installed at the bottom of the buffer rod 3 on the same side, a disassembly and assembly component is provided between the bottom of the buffer rod 3 and the wear-resistant plate 4, the upper end of the buffer rod 3 is located in the landing gear 2, and is provided with a buffer component.

[0019] The buffer assembly includes a cavity 21 and a piston plate 22. The cavity 21 is opened at the bottom of the landing gear 2 and is aligned with the buffer rod 3. The piston plate 22 is slidably connected in the cavity 21. The upper end of the buffer rod 3 is located in the cavity 21 and is fixed on the piston plate 22. A reset spring is fixed between the bottom of the piston plate 22 and the bottom of the cavity 21. A pressure relief hole 23 is opened on the side wall of the upper end of the cavity 21.

[0020] The disassembly and assembly components include an elliptical plate 32 and a card slot 43. A connecting block 31 is fixed to the bottom of the buffer rod 3. The elliptical plate 32 is rotatably connected to the bottom of the connecting block 31. An adapting groove 41 is provided at the upper end of the wear-resistant plate 4 and aligned with the buffer rod 3. A card slot 43 is provided at the bottom of the wear-resistant plate 4 and corresponding to the adapting groove 41. A connecting hole 42 is provided between the card slot 43 and the adapting groove 41. The elliptical plate 32 passes through the connecting hole 42 and is clamped in the card slot 43. The connecting block 31 and the elliptical plate 32 are elliptical structures of the same size and the same size as the connecting hole 42. The adapting groove 41 and the card slot 43 are both circular structures and the same size as the buffer rod 3. The diameter of the card slot 43 is the same as the long diameter of the elliptical plate 32. A rotating shaft is provided between the elliptical plate 32 and the connecting block 31, and a torsion spring is installed at the connection.

[0021] Working principle: When the UAV fails to land at high altitude, the speed increases continuously under the influence of gravity acceleration. After reaching the predetermined value, the speed sensor and the controller can be used to automatically open the parachute bag 11 to achieve the purpose of speed reduction protection. After opening, it can ensure that the landing frame 2 is always facing downward and finally contacts the ground. During this process or during normal landing, before the landing frame 2 contacts the ground, the wear-resistant plate 4 at the bottom will first contact the ground, squeeze the buffer rod 3 upward, drive the piston plate 22 to squeeze upward, and then increase the air pressure in the cavity 21 to achieve the purpose of buffering. When the gas in the cavity 21 is compressed, the gas will be slowly discharged from the pressure relief hole 23 without affecting the buffering. In this case, the rebound speed is reduced, thereby reducing the risk of the drone bouncing after landing. Since the entire landing gear 2 is in contact with the ground, the wear-resistant plate 4 will not cause wear to the landing gear 2. Therefore, when replacing parts, only the wear-resistant plate 4 needs to be replaced. During operation, the elliptical plate 32 is rotated, and the elliptical plate 32 is aligned with the connecting block 31 while twisting the torsion spring. At this time, the elliptical plate 32 can be pulled out or inserted along the perforation. After the elliptical plate 32 is inserted into the card slot 43, the torsion spring is reset to align the position of the elliptical plate 32 with the perforation position, thereby achieving the purpose of clamping and fixing, completing the combination of the wear-resistant plate 4 and the buffer rod 3, simple operation, and ensuring installation stability.

[0022] It should be noted that, in this document, relational terms such as first and second, etc., are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "comprises," "comprising," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that includes a list of elements includes not only those elements but also other elements not explicitly listed, or elements inherent to such process, method, article, or apparatus.

[0023] Although the embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and variations may be made to these embodiments without departing from the principles and spirit of the present invention, and the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A UAV with a landing cushion structure, comprising a fuselage (1) and a landing gear (2), characterized in that: A speed sensor and a controller are installed in the fuselage (1); a parachute bag (11) electrically connected to the controller is fixed on the upper end of the fuselage (1); a parachute (12) is arranged in the parachute bag (11); the landing rack (2) is fixed to the bottom of the fuselage (1) and is symmetrically distributed; the landing rack (2) is a U-shaped structure, and a buffer rod (3) is installed at the bottom; a wear-resistant plate (4) is installed at the bottom of the buffer rod (3) on the same side; a disassembly assembly is arranged between the bottom of the buffer rod (3) and the wear-resistant plate (4); the upper end of the buffer rod (3) is located in the landing rack (2) and is provided with a buffer assembly.

2. The UAV with a landing cushion structure according to claim 1, characterized in that: The buffer assembly comprises a cavity (21) and a piston plate (22). The cavity (21) is opened at the bottom of the landing gear (2) and is aligned with the buffer rod (3). The piston plate (22) is slidably connected in the cavity (21). The upper end of the buffer rod (3) is located in the cavity (21) and is fixed on the piston plate (22).

3. The UAV with a landing cushion structure according to claim 2, characterized in that: A return spring is fixed between the bottom of the piston plate (22) and the bottom of the cavity (21), and a pressure relief hole (23) is provided on the upper side wall of the cavity (21).

4. The UAV with a landing cushion structure according to claim 1, characterized in that: The disassembly and assembly component comprises an elliptical plate (32) and a clamping groove (43); a connecting block (31) is fixed to the bottom of the buffer rod (3); the elliptical plate (32) is rotatably connected to the bottom of the connecting block (31); an adapting groove (41) is provided at the upper end of the wear-resistant plate (4) and aligned with the buffer rod (3); a clamping groove (43) is provided at the bottom of the wear-resistant plate (4) and corresponding to the adapting groove (41); a connecting hole (42) is provided between the clamping groove (43) and the adapting groove (41); the elliptical plate (32) passes through the connecting hole (42) and is clamped in the clamping groove (43).

5. The UAV with a landing cushion structure according to claim 4, characterized in that: The connecting block (31) and the elliptical plate (32) are elliptical structures of the same size and have the same size as the connecting hole (42); the adapting groove (41) and the clamping groove (43) are both circular structures and have the same size as the buffer rod (3); the diameter of the clamping groove (43) is the same as the major diameter of the elliptical plate (32).

6. The UAV with a landing buffer structure according to claim 4, characterized in that: A rotating shaft is provided between the elliptical plate (32) and the connecting block (31), and a torsion spring is installed at the connection.

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