Unmanned aerial vehicle with landing buffer device and system

Abstract

The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to an unmanned aerial vehicle with a landing buffering device and a system, the landing buffering system comprises a connecting plate, the connecting plate is of a frame-shaped structure as a whole, and a plurality of buffering mechanisms are arranged in the direction matched with each wing of the unmanned aerial vehicle; the buffer mechanism comprises an extension arm, a damping cylinder and a supporting claw, the extension arm is integrally connected with the connecting plate, the damping cylinder is connected with the other end of the extension arm, and the supporting claw is connected with the damping cylinder and is obliquely and inwards buckled in the axis direction of the extension arm. The damage to the body is reduced.

Description

Technical Field

[0001] The invention belongs to the technical field of unmanned aerial vehicles, and in particular relates to an unmanned aerial vehicle with a landing buffer device and a system thereof. Background Art

[0002] Currently in the field of drones, with the maturity of technology, the flight and take-off and landing speeds of drones have reached a relatively high speed, especially for high-speed shuttles and some heavy agricultural drones. Due to their high-speed movement or heavy weight during take-off and landing, these drones will generate a large impact force with the ground when landing, which can easily cause a large impact force on the drone body, causing the internal components of the drone to be easily damaged or other parts to be damaged due to vibration, which is not conducive to the stable operation and use of the drone. Summary of the invention

[0003] The purpose of the present invention is to provide a drone and a system with a landing buffer device, so as to solve the problems mentioned in the background technology.

[0004] In order to achieve the above technical objectives, the technical solution adopted by the present invention is as follows:

[0005] A landing buffer system comprises a connecting plate, wherein the connecting plate is in a frame-shaped structure as a whole and is provided with a plurality of buffer mechanisms in each wing direction of a matching drone;

[0006] The buffer mechanism includes an extension arm, a damping cylinder and a supporting claw. The extension arm is integrally connected to the connecting plate, the damping cylinder is connected to the other end of the extension arm, and the supporting claw is connected to the damping cylinder and is tilted inward along the axial direction of the extension arm.

[0007] The damping cylinder includes a cylinder body, a first plug body, a sliding shaft, a first spring and a liquid storage bag. The cylinder body is connected to the extension arm. The first plug body is slidingly sealed and arranged in the cylinder body. The sliding shaft is concentrically connected to the first plug body and slides out of the lower end of the cylinder body to be connected to the supporting claw. The first spring is arranged at the other end of the first plug body and is located in the cylinder body. The liquid storage bag is embedded in the extension arm. A throttling liquid hole is commonly opened between the cylinder body and the extension arm, and the liquid storage bag is connected to the throttling liquid hole correspondingly.

[0008] A shock absorbing assembly is also provided between the upper end of the connecting plate and the damping cylinder. The shock absorbing assembly includes an air replenisher and a shock absorbing airbag. An interlocking groove is provided on the upper end of the connecting plate. The shock absorbing airbag is embedded in the interlocking groove. The air replenisher is provided on the extension arm and connected to the air path of the shock absorbing airbag.

[0009] The air replenisher includes a catheter, a second plug body, a second spring, a one-way air intake valve and a one-way exhaust valve. When the air replenisher is provided, the liquid storage bag is a catheter, and the catheter is a hard tubular structure. The second plug body is slidingly sealed and arranged in the catheter. The second spring is connected to the plug body and is located on the side of the catheter away from the cylinder body. The one-way air intake valve and the one-way exhaust valve are both arranged at the other end of the catheter. The one-way air intake valve is connected to the outside world, and the one-way exhaust valve is connected to the shock-absorbing airbag.

[0010] The shock-absorbing airbag is also provided with a pressure relief valve.

[0011] A limiting ring is also provided on the upper side of the cylinder body, and the limiting ring is located on the lower side of the throttling liquid hole between the conduit and the cylinder body.

[0012] A UAV with a landing buffer device comprises a UAV body and a landing buffer system, wherein the landing buffer system is arranged at the lower end of the UAV.

[0013] Compared with the prior art, the present invention has at least the following advantages:

[0014] Through the setting of the damping cylinder, when the UAV lands, the dual effects of the hydraulic oil flow resistance and the spring elastic deformation can effectively absorb the impact energy of the UAV during landing and reduce the damage to the body. The inclined inward buckled support claw design can disperse the impact force and cooperate with the axial movement of the damping cylinder to further enhance the buffering effect. Through the linkage between the shock-absorbing airbag and the air inflator, the airbag is automatically inflated during landing to enhance the buffering performance. During takeoff, negative pressure reset and air replenishment are used to ensure that the airbag is always in the best inflation state to meet the needs of multiple take-offs and landings. The pressure relief valve prevents the airbag from being overfilled and improves the safety of the system. The hydraulic system (liquid storage bag, throttling liquid hole) and the pneumatic system (shock-absorbing airbag, air inflator) are integrated into the extension arm and the connecting plate to reduce the additional space occupation and achieve lightweight design. The buffer system can be flexibly adapted to different models of UAVs, and by adjusting parameters such as hydraulic oil viscosity and spring stiffness, it can adapt to various landing scenarios (such as hard ground, grass, etc.). In some embodiments, it can also cooperate with the blade protection cover set on the UAV to realize the integrated installation of the protection module of the entire UAV group. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The present invention is further illustrated by means of the non-limiting examples given in the accompanying drawings.

[0016] Figure 1 It is a structural schematic diagram of the landing buffer system of the present invention.

[0017] Figure 2 It is a structural cross-sectional view of the landing buffer system of the present invention.

[0018] The connecting plate 1 , the extension arm 11 , the supporting claw 12 , the cylinder 2 , the first plug body 21 , the sliding shaft 22 , the first spring 23 , the limiting ring 24 , the shock absorbing airbag 3 , the conduit 4 , the second plug body 41 , and the second spring 42 . DETAILED DESCRIPTION

[0019] In order to enable those skilled in the art to better understand the present invention, the technical solution of the present invention is further described below in conjunction with the accompanying drawings and embodiments.

[0020] Example 1: Figure 1-2 As shown, a landing buffer system includes a connecting plate 1, the connecting plate 1 is a frame-shaped structure as a whole and is provided with a plurality of buffer mechanisms in each wing direction of the UAV;

[0021] The buffer mechanism includes an extension arm 11, a damping cylinder and a supporting claw 12. The extension arm 11 is integrally connected to the connecting plate 1, the damping cylinder is connected to the other end of the extension arm 11, and the supporting claw 12 is connected to the damping cylinder and tilted inward along the axial direction of the extension arm 11.

[0022] When using the landing buffer system, the connecting plate 1 can be connected to the drone by bolts or magnetic buckles, etc., which can achieve quick connection. When the drone lands, the support claws 12 play a supporting role in contacting the ground, and the damping cylinder connected to the support claws 12 can weaken and absorb the upward impact force generated during landing, so as to reduce the damage to the drone body caused by the impact during landing.

[0023] The damping cylinder includes a cylinder 2, a first plug body 21, a sliding shaft 22, a first spring 23 and a liquid storage bag. The cylinder 2 is connected to the extension arm 11. The first plug body 21 is slidingly sealed in the cylinder 2. The sliding shaft 22 is concentrically connected to the first plug body 21 and slides out of the lower end of the cylinder 2 to be connected to the supporting claw 12. The first spring 23 is arranged at the other end of the first plug body 21 and is located in the cylinder 2. The liquid storage bag is embedded in the extension arm 11. A throttling liquid hole is commonly opened between the cylinder 2 and the extension arm 11, and the liquid storage bag is connected to the throttling liquid hole correspondingly.

[0024] A limiting ring 24 is also provided on the inner upper side of the cylinder 2 , and the limiting ring 24 is located on the lower side of the throttling liquid hole between the conduit 4 and the cylinder 2 .

[0025] When the drone is landing, the support claw 12 contacts the ground and generates an upward impact force. At this time, the impact force acts on the sliding shaft 22 and the first plug body 21, thereby causing the first plug body 21 to move upward. The upper side of the first plug body 21 in the cylinder 2 is completely filled with hydraulic oil between the liquid storage bag. At this time, the upward movement of the first plug body 21 will squeeze the liquid through the throttling liquid hole into the liquid storage bag for storage. In this process, the throttling of the flow of hydraulic oil by the throttling liquid hole can absorb and weaken the impact force of the support claw 12 contacting the ground. At the same time, the first spring 23 is squeezed by the first plug body 21, and its contraction The reaction force of contraction can also absorb and weaken the impact force, thereby achieving a buffering effect. After takeoff, the first plug body 21 is pushed back by the first spring 23, and the downward movement of the first plug body 21 produces a suction effect, so that the hydraulic oil in the reservoir can be drawn out and reset to meet the needs of the next landing. At the same time, since the first spring 23 and the throttling fluid hole themselves have a certain supporting strength, when the descent speed of the drone is relatively low, the upward movement stroke of the support claw 12 will not be too large to affect the overall height of the drone from the ground in a relatively stable state.

[0026] Example 2: Figure 1-2 As shown, based on the further improvement of Example 1, a shock absorbing assembly is further provided between the upper end of the connecting plate 1 and the damping cylinder, the shock absorbing assembly includes an air replenisher and a shock absorbing airbag 3, an interlocking groove is opened at the upper end of the connecting plate 1, the shock absorbing airbag 3 is embedded in the interlocking groove, the air replenisher is provided on the extension arm 11 and is connected to the air path of the shock absorbing airbag 3.

[0027] The air replenisher includes a conduit 4, a second plug body 41, a second spring 42, a one-way air intake valve and a one-way exhaust valve. When the air replenisher is provided, the liquid storage bag is the conduit 4, the conduit 4 is a hard tubular structure, the second plug body 41 is slidingly sealed and arranged in the conduit 4, the second spring 42 is connected to the plug body and is located in the conduit 4 on the side away from the cylinder 2, the one-way air intake valve and the one-way exhaust valve are both arranged at the other end of the conduit 4, the one-way air intake valve is connected to the outside, and the one-way exhaust valve is connected to the shock-absorbing airbag 3.

[0028] The shock absorbing airbag 3 is also provided with a pressure relief valve.

[0029] Furthermore, in order to improve the impact absorption effect between the connecting plate 1 and the drone, the shock-absorbing airbag 3 at the upper end of the connecting plate 1 can weaken and isolate the kinetic energy transmission between the connecting plate 1 and the drone. Since the shock-absorbing airbag 3 itself has a certain elasticity and cushioning property, the shock-absorbing airbag 3 can be further weakened after being set up in this way. In order to meet the effects of isolation and connection, the width and thickness of the shock-absorbing airbag 3 can be expanded to increase the area and thickness covered between the connecting plate 1 and the drone to achieve a further cushioning effect.

[0030] In order to ensure that the expandability of the shock-absorbing airbag 3 can meet the needs of shock absorption, each time the drone lands, when the hydraulic oil is input into the conduit 4, the closure of the liquid circuit will force the second plug 41 to move. At this time, the air in the space of the second plug 41 away from the side of the cylinder 2 will be input into the shock-absorbing airbag 3 through the one-way exhaust valve, thereby replenishing the expandability of the shock-absorbing airbag 3 to ensure that the inflated state is maintained in real time. When the hydraulic oil is retracted into the cylinder 2, the second plug 41 is reset by negative pressure suction, and with the push of the second spring 42, external air can be replenished into the conduit 4. The pressure relief valve can ensure that the shock-absorbing airbag 3 will not be overfilled. At the same time, in the inflated state, the pressure relief valve and the expansion needs of the shock-absorbing airbag 3 can further generate buffering resistance, thereby further reducing the impact damage to the drone during landing.

[0031] A UAV with a landing buffer device comprises a UAV body and a landing buffer system, wherein the landing buffer system is arranged at the lower end of the UAV.

[0032] The above embodiments are merely illustrative of the principles and effects of the present invention, and are not intended to limit the present invention. Anyone familiar with the technology may modify or change the above embodiments without violating the spirit and scope of the present invention. Therefore, all equivalent modifications or changes made by those with ordinary knowledge in the technical field without departing from the spirit and technical ideas disclosed by the present invention should still be covered by the claims of the present invention.

Claims

1. A landing buffer system, comprising a connecting plate, characterized in that: The connecting plate is in a frame-shaped structure as a whole and is provided with a plurality of buffer mechanisms in each wing direction of the UAV; The buffer mechanism includes an extension arm, a damping cylinder and a supporting claw. The extension arm is integrally connected to the connecting plate, the damping cylinder is connected to the other end of the extension arm, and the supporting claw is connected to the damping cylinder and is tilted inward along the axial direction of the extension arm.

2. A landing cushioning system according to claim 1, characterized in that: The damping cylinder includes a cylinder body, a first plug body, a sliding shaft, a first spring and a liquid storage bag. The cylinder body is connected to the extension arm. The first plug body is slidingly sealed and arranged in the cylinder body. The sliding shaft is concentrically connected to the first plug body and slides out of the lower end of the cylinder body to be connected to the supporting claw. The first spring is arranged at the other end of the first plug body and is located in the cylinder body. The liquid storage bag is embedded in the extension arm. A throttling liquid hole is commonly opened between the cylinder body and the extension arm, and the liquid storage bag is connected to the throttling liquid hole correspondingly.

3. A landing cushioning system according to claim 2, characterized in that: A shock absorbing assembly is also provided between the upper end of the connecting plate and the damping cylinder. The shock absorbing assembly includes an air replenisher and a shock absorbing airbag. An interlocking groove is provided on the upper end of the connecting plate. The shock absorbing airbag is embedded in the interlocking groove. The air replenisher is provided on the extension arm and connected to the air path of the shock absorbing airbag.

4. A landing cushioning system according to claim 3, characterized in that: The air replenisher includes a catheter, a second plug body, a second spring, a one-way air intake valve and a one-way exhaust valve. When the air replenisher is provided, the liquid storage bag is a catheter, and the catheter is a hard tubular structure. The second plug body is slidingly sealed and arranged in the catheter. The second spring is connected to the plug body and is located on the side of the catheter away from the cylinder body. The one-way air intake valve and the one-way exhaust valve are both arranged at the other end of the catheter. The one-way air intake valve is connected to the outside world, and the one-way exhaust valve is connected to the shock-absorbing airbag.

5. A landing cushioning system according to claim 4, characterized in that: The shock-absorbing airbag is also provided with a pressure relief valve.

6. A landing cushioning system according to claim 5, characterized in that: A limiting ring is also provided on the upper side of the cylinder body, and the limiting ring is located on the lower side of the throttling liquid hole between the conduit and the cylinder body.

7. A drone with a landing buffer device, characterized in that: It comprises a drone body and a landing cushion system as described in any one of claims 1 to 6, wherein the landing cushion system is arranged at the lower end of the drone.

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