An unmanned aerial vehicle with anti-collision structure

Abstract

The application discloses a kind of unmanned aerial vehicle with anti-collision structure, comprising: fuselage, landing gear, rotor, first anti-collision device, second anti-collision device, the fuselage is unmanned aerial vehicle main body, carries unmanned aerial vehicle basic component;The landing gear square distribution is provided with four, is fixed in the four corners of fuselage;The rotor square distribution is provided with four, respectively rotatable fixed in the top of landing gear;The first anti-collision device square distribution is provided with four, and the middle part of each first anti-collision device is respectively fixed in the top of landing gear;The second anti-collision device is provided with four, respectively between adjacent first anti-collision device, and fixed on fuselage.Compared with prior art, the anti-collision device in the application adopts the structure design of mitigation offset, multiple rotating structures, so that the unmanned aerial vehicle is more flexible and variable in response to impact, and reduces the loss of unmanned aerial vehicle main body.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of unmanned aerial vehicles, and more particularly to an unmanned aerial vehicle with an anti-collision structure. BACKGROUND

[0002] An unmanned aerial vehicle, referred to as a "drone" for short, is an unmanned aircraft that is controlled by using radio remote control equipment and self-provided program control devices. During the flight of the unmanned aerial vehicle, the propeller rotates at a high speed and is very easy to collide with the outside world, resulting in loss of control, crash, and even injury, especially in a relatively narrow and complex environment. The unmanned aerial vehicle is difficult to enter, and even if it enters, it is prone to be hit and crash. The existing anti-collision structure of the unmanned aerial vehicle has limited impact resistance and cannot flexibly cope with impacts in different situations. Therefore, it is necessary to provide an unmanned aerial vehicle with an anti-collision structure to solve the problems raised in the background. SUMMARY

[0003] To achieve the above-mentioned purpose, the present application provides the following technical scheme: an unmanned aerial vehicle with an anti-collision structure, comprising:

[0004] a fuselage, which is the main body of the unmanned aerial vehicle and carries the basic components of the unmanned aerial vehicle;

[0005] a landing device, which is arranged in a square distribution and has four landing devices, is fixed to the four corners of the fuselage, and is controlled by the fuselage as a whole;

[0006] a rotor, which is arranged in a square distribution and has four rotors, is rotatably fixed to the top of the landing device, and is rotated by the fuselage;

[0007] a first anti-collision device, which is arranged in a square distribution and has four first anti-collision devices, is fixed to the top of the landing device;

[0008] a second anti-collision device, which is arranged in a square distribution and has four second anti-collision devices, is arranged between adjacent first anti-collision devices and is fixed to the fuselage.

[0009] Further, as a preferred embodiment, the first anti-collision device comprises:

[0010] a reset bearing, which is fixed to the top of the landing device;

[0011] a connecting rod, which is arranged in a ring distribution and has a plurality of connecting rods, is fixed to the outer wall of the reset bearing;

[0012] a shock-absorbing ring, which is arranged concentrically with the reset bearing and is fixedly connected with the connecting rod, rotates and resets through the reset bearing under the action of the connecting rod when the shock-absorbing ring is hit, to relieve and offset the impact force.

[0013] Further, as a preferred embodiment, the reset bearing comprises:

[0014] The outer shaft is fixed with the outer wall and the connecting rod.

[0015] The inner shaft is fixed at the top of the landing device, and the rotating shaft at the bottom of the rotor is rotatably fixed on the landing device through the center of the inner shaft.

[0016] The compression spring is arc-shaped and symmetrically arranged in two sections between the outer shaft and the inner shaft.

[0017] The pressing plate is symmetrically arranged in two sections and fixed on the inner wall of the outer shaft, and is slidably connected with the outer wall of the inner shaft. When the shock-absorbing ring rotates, it drives the outer shaft to rotate, and then drives the pressing plate to rotate on the inner shaft, compressing the compression spring. The elastic force generated during compression also plays a certain role in offsetting the impact force.

[0018] The spacer plate is arranged on the central axis between the two pressing plates, between the outer shaft and the inner shaft, and at the junction of the two compression springs, providing a pressure support point for the compression springs on both sides.

[0019] Further, as a preferred embodiment, the inner wall of the outer shaft is provided with a unique bayonet corresponding to the spacer plate, and the outer wall of the inner shaft is provided with multiple bays corresponding to the spacer plate. When the spacer plate is fixed on the inner shaft through the bayonet, the spacer plate is subjected to pressure from the compression spring, and the shock-absorbing ring is in a rotating reset state. After resetting, the spacer plate is always in a corresponding state with the bayonet on the outer shaft. When the spacer plate is fixed on the outer shaft through the bayonet, the spacer plate and the pressing plate are fixed on the same shaft at this time, and the shock-absorbing ring is in a sustainable rotating state. In the rotating state, the stop position is uncertain, and the multiple bays on the inner shaft provide a certain convenience for switching between working modes.

[0020] Further, as a preferred embodiment, the bayonet is provided with a pop-up fixing device corresponding to the spacer plate, which is assisted by a monitoring system provided in the fuselage. The pop-up fixing device is popped up according to the judgment of the impact object and fixed. When impacted by a flying object, the spacer plate is fixed on the inner shaft and protected by the buffer offsetting effect. When impacted by a large fixed object, the bayonet of the inner shaft pops up the spacer plate, which is fixed by the bayonet on the outer shaft, and avoids by continuously rotating on the object.

[0021] Further, as a preferred embodiment, the inner wall of the inner ring of the shock-absorbing ring is fixedly connected with the connecting rod, and the outer wall is connected with the inner wall of the outer ring through an elastic member. The outer ring is a first stress surface made of rubber and has a certain buffering property, so that the impact force is transmitted to the elastic member, further causing the shock-absorbing ring to rotate and reduce pressure.

[0022] Further, as a preferred embodiment, the elastic member is arranged in a ring shape and has multiple sections fixed in the middle of the shock-absorbing ring. The uniformly distributed elastic members provide sufficient buffer space for impact.

[0023] Further, as a preferred embodiment, the second anti-collision device comprises:

[0024] frame body, fixed on the machine body;

[0025] universal joint, fixed inside the frame body, and elastically connected with the upper and lower inner walls of the frame body through the supporting spring, which plays a stabilizing role on the universal joint and resets in time after upward and downward rotation;

[0026] connecting shaft, in a telescopic structure, controlled by the machine body 1 through electricity, and telescoped according to the impact situation, fixedly connected with the universal joint, and located at the middle part of the adjacent two first anti-collision devices, driving the universal joint to move;

[0027] supporting rod, in a V-shaped distribution, with the angle end slidably fixed on the connecting shaft through a circular ring, moving synchronously with the connecting shaft, and sliding along with the telescoping of the connecting shaft;

[0028] anti-collision plate, in an arc surface, fixedly connected with the extending end of the connecting shaft at the center, and fixedly connected with the open end of the supporting rod at both ends, and having a certain safety distance with the two sides of the shock-absorbing ring, after being impacted, transmitting the impact force to the universal joint through the connecting shaft according to the impact angle, and then rotating the universal joint, while the anti-collision plate moves with the universal joint to bounce the impact object.

[0029] Further, as a preferred, the circular ring is fixedly connected with the angle end of the supporting rod, and slidably connected with the outer wall of the connecting shaft, when the connecting shaft extends or retracts, the circular ring moves on the outer wall of the connecting shaft along with the supporting rod.

[0030] Further, as a preferred, the anti-collision plate is provided with a buffer spring inside, and a wear-resistant flat surface outside, when the impact object hits the second anti-collision device, the anti-collision plate itself buffers, and if the force is too large, drives the universal joint to rotate and bounce to avoid.

[0031] Compared with the prior art, the beneficial effects of the present application are:

[0032] In the present application, the first anti-collision device is provided to protect the unmanned aerial vehicle rotor, and the cooperation of the shock-absorbing ring and the reset rotating shaft enables the unmanned aerial vehicle to make a relief and offset response mode during the impact, the continuous rotation of the shock-absorbing ring and the switching of the rotating reset mode enable the unmanned aerial vehicle to cope with various impacts and reduce the probability of damage to the unmanned aerial vehicle.

[0033] In the present application, the second anti-collision device is provided to protect the unmanned aerial vehicle body, reduce the flight resistance, and for obstacles with large impact force, the second anti-collision device is used for the second buffering and bouncing after passing through the first anti-collision device, further ensuring the safety of the unmanned aerial vehicle. BRIEF DESCRIPTION OF DRAWINGS

[0034] Fig. 1 It is a whole structure schematic diagram of an unmanned aerial vehicle with an anti-collision structure;

[0035] Fig. 2 It is a plane schematic diagram of a UAV with anti-collision structure;

[0036] Fig. 3 It is a reset bearing structure schematic diagram in a UAV with anti-collision structure;

[0037] Fig. 4 It is a second anti-collision device schematic diagram in a UAV with anti-collision structure;

[0038] Fig. 5 It is a second anti-collision device extension state schematic diagram in a UAV with anti-collision structure;

[0039] In the figure: 1, fuselage; 2, landing device; 3, rotor; 4, first anti-collision device; 5, second anti-collision device; 41, reset bearing; 42, connecting rod; 43, shock ring; 51, frame; 52, universal joint; 53, connecting shaft; 54, support rod; 55, anti-collision plate; 56, support spring; 57, circular ring; 411, outer shaft; 412, inner shaft; 413, compression spring; 414, pressing plate; 415, pad; 416, bayonet; 431, outer ring; 432, elastic member; 433, inner ring. DETAILED DESCRIPTION

[0040] Please refer to Figs. 1-5 , in the embodiment of the application, a UAV with anti-collision structure comprises:

[0041] Fuselage 1, as the main body of the UAV, carries the basic components of the UAV;

[0042] Landing device 2, four are arranged in a square distribution and are fixed to the four corners of fuselage 1, and are controlled by fuselage 1;

[0043] Rotor 3, four are arranged in a square distribution and are respectively rotatably fixed to the top of landing device 2, and are rotatably driven by fuselage 1;

[0044] First anti-collision device 4, four are arranged in a square distribution, and the middle part of each first anti-collision device 4 is respectively fixed to the top of landing device 2;

[0045] Second anti-collision device 5, four are arranged, are respectively distributed between adjacent first anti-collision devices 4, and are fixed to fuselage 1.

[0046] In the embodiment, the first anti-collision device 4 comprises:

[0047] Reset bearing 41, fixed to the top of landing device 2;

[0048] Connecting rod 42, a plurality of are arranged in a ring distribution and are fixed to the outer wall of reset bearing 41;

[0049] The shock-absorbing ring 43 is arranged concentrically with the reset bearing 41 and is fixedly connected with the connecting rod 42. When the shock-absorbing ring 43 is impacted, the shock-absorbing ring 43 rotates and resets through the reset bearing 41 under the action of the connecting rod 42, so as to relieve and offset the impact force.

[0050] In the embodiment, the reset bearing 41 comprises:

[0051] The outer shaft 411 is fixedly connected with the connecting rod 42.

[0052] The inner shaft 412 is fixed at the top of the landing device 2, and the rotating shaft at the bottom of the rotor 3 is rotatably fixed to the landing device 2 through the center of the inner shaft 412.

[0053] The compression spring 413 is arranged in two symmetrical arcs between the outer shaft 411 and the inner shaft 412.

[0054] The pressing plate 414 is arranged in two symmetrical plates and is fixedly connected with the inner wall of the outer shaft 411 and the outer wall of the inner shaft 412. When the shock-absorbing ring 43 rotates, the outer shaft 411 rotates, and the pressing plate 414 rotates on the inner shaft 412, thereby compressing the compression spring 413. The elastic force generated in the compression process also offsets the impact force.

[0055] The gusset plate 415 is arranged on the central axis between the two pressing plates 414, between the outer shaft 411 and the inner shaft 412, and at the joint of the two compression springs 413, thereby providing a pressure support point for the two compression springs 413.

[0056] In the embodiment, the inner wall of the outer shaft 411 is provided with a unique bayonet 416 corresponding to the gusset plate 415, and the outer wall of the inner shaft 412 is provided with a plurality of bayonets 416 corresponding to the gusset plate 415. When the gusset plate 415 is fixed to the inner shaft 412 through the bayonet 416, the gusset plate 415 is subjected to pressure from the compression spring 413, and the shock-absorbing ring 43 is in a rotating reset state. After resetting, the gusset plate 415 is always in a corresponding state with the bayonet 416 on the outer shaft 411. When the gusset plate 415 is fixed to the outer shaft 411 through the bayonet 416, the gusset plate 415 and the pressing plate 414 are fixed on the same shaft at this time, and the shock-absorbing ring 43 is in a sustainable rotating state. In the rotating state, the stop position is uncertain, and the plurality of bayonets 416 on the inner shaft 412 provide convenience for switching between working modes.

[0057] In the embodiment, the bayonet 416 is internally provided with a pop-up fixing device corresponding to the backing plate 415, which is assisted by a monitoring system provided in the fuselage 1 to make a judgment for pop-up fixing according to the impact object. When impacted by a flying object, the backing plate 415 is fixed on the inner shaft 412 to be protected by the buffering effect. When impacted by a large object, the backing plate 415 is popped up by the bayonet 416 of the inner shaft 412 and is fixed by the bayonet 416 on the outer shaft 411 to be avoided by continuously rotating on the object.

[0058] In the embodiment, the inner wall of the inner ring 433 of the damping ring 43 is fixedly connected with the connecting rod 42, and the outer wall is connected with the inner wall of the outer ring 431 through the elastic member 432. The outer ring 431 serves as a first stress surface and is made of rubber material and has a certain buffering property. Then the impact force is transmitted to the elastic member 432 to further cause the damping ring 43 to rotate for pressure reduction.

[0059] In the embodiment, the elastic member 432 is annularly distributed and arranged in multiple numbers and is fixed in the middle of the damping ring 43. The uniformly distributed elastic members 432 provide sufficient buffer allowance for impact.

[0060] In the embodiment, the second anti-collision device 5 comprises:

[0061] The frame body 51 is fixed on the fuselage 1.

[0062] The universal joint 52 is fixed inside the frame body 51 and is elastically connected with the upper and lower inner walls of the frame body 51 through the supporting spring 56 to stabilize the universal joint 52 and reset in time after upward and downward rotation.

[0063] The connecting shaft 53 is of a telescopic structure and is controlled by electricity of the fuselage 1 to be telescoped according to the impact condition. The connecting shaft 53 is fixedly connected with the universal joint 52 and is located at the middle part of the adjacent two first anti-collision devices 4 to drive the universal joint 52 to move.

[0064] The supporting rod 54 is V-shapedly distributed, the angle end is slidably fixed on the connecting shaft 53 through the circular ring 57, synchronously moves with the connecting shaft 53, and slides with the connecting shaft 53 to be telescoped.

[0065] The anti-collision plate 55 is arc-shaped, the center is fixedly connected with the protruding end of the connecting shaft 53, and the two arc-shaped ends are fixedly connected with the open ends of the supporting rod 54. There is a certain safety distance between the anti-collision plate 55 and the two damping rings 43. After being impacted, the impact force is transmitted to the universal joint 52 through the connecting shaft 53 according to the impact angle, the universal joint 52 rotates, and the anti-collision plate 55 moves with the universal joint 52 to pop up the impact object.

[0066] In the embodiment, the circular ring 57 is fixedly connected with the support rod 54 at an angle, and is slidably connected with the outer wall of the connecting shaft 53, when the connecting shaft 53 is extended or retracted, the circular ring 57 moves on the outer wall of the connecting shaft 53 along with the support rod 54.

[0067] In the embodiment, the anti-collision plate 55 is internally provided with a buffer spring, and the outer side is a wear-resistant plane, when the impact object hits the second anti-collision device 5, the anti-collision plate 55 itself buffers, if the force is too large, the universal joint 52 is driven to rotate, and the impact object is bounced away.

[0068] In the specific implementation, the internal monitoring system of the fuselage 1 assists in the work, when facing large impact objects (such as walls, etc.), the reset bearing 41 of the first anti-collision device 4 is switched to a continuously rotating state, during the operation of the unmanned aerial vehicle, the first anti-collision device 4 rotates on the impact object to avoid, at this time, the second anti-collision device 5 always maintains a fixed state; when facing small impact objects (the volume is less than one-third of the unmanned aerial vehicle), when the impact force is sufficient, the following anti-collision process should be gone through, the unmanned aerial vehicle monitoring system finds that the impact object cannot be avoided, quickly adjusts the angle of the unmanned aerial vehicle itself, so that the first anti-collision device 4 first bears the impact, at the same time, under the operation of the internal system of the fuselage 1, the second anti-collision device 5 is extended under the action of the connecting shaft 53, at this time, the reset bearing 41 is in a rotating reset state, the impact force is buffered by the outer ring 431 and the elastic element 432 of the shock-absorbing ring 43, and part of the impact force is offset, and then the shock-absorbing ring 43 rotates to compress the compression spring 413 to offset part of the impact force, and then under the rotating action, the impact object enters the second anti-collision device 5, the first anti-collision device 4 is reset, in the second anti-collision device 5, the impact force is further reduced by the surface and internal buffer spring of the anti-collision plate 55, and then under the action of the impact force, the universal joint 52 rotates according to the contact position of the impact object to offset the impact force and bounce the impact object away or avoid it, and then the second anti-collision device 5 is retracted to reduce the flight resistance, and the unmanned aerial vehicle resumes normal flight.

[0069] The above is only the preferred specific embodiment of the present application, but the protection scope of the present application is not limited to this, any person skilled in the art can make equivalent replacement or change according to the technical scheme and the inventive concept of the present application within the technical range disclosed by the present application, which should be covered in the protection scope of the present application.

Claims

1. A drone with anti-collision structure, characterized in that: The utility model relates to a kind of unmanned aerial vehicle, including: Machine body (1), as unmanned aerial vehicle main body, carries unmanned aerial vehicle basic component; Landing gear (2), four are arranged in square distribution, are fixed in the four corners of machine body (1); Rotor (3), four are arranged in square distribution, respectively rotatable fixed in the top of landing gear (2); First anti-collision device (4), four are arranged in square distribution, and the middle part of each first anti-collision device (4) is respectively fixed in the top of landing gear (2); Second anti-collision device (5), four are arranged, respectively between adjacent first anti-collision device (4), and fixed on machine body (1); The first anti-collision device (4) includes: Reset bearing (41), fixed in the top of landing gear (2); Connecting rod (42), annular distribution is provided with multiple, is fixed in the outer wall of reset bearing (41); Damping ring (43), concentric with reset bearing (41) is arranged, and is fixedly connected with connecting rod (42); The reset bearing (41) includes: Outer shaft (411), outer wall is fixed with connecting rod (42); Inner shaft (412), fixed in the top of landing gear (2), and the bottom rotating shaft of rotor (3) is rotatable fixed in landing gear (2) by passing through the center of inner shaft (412); Compression spring (413), arc, two segments are symmetrically arranged, between outer shaft (411) and inner shaft (412); Pressing plate (414), symmetrically arranged two, are fixed on the inner wall of outer shaft (411), and are slidably connected with the outer wall of inner shaft (412); Pad (415), is arranged on the central axis between the two pressing plates (414), between outer shaft (411) and inner shaft (412), and is located at the intersection of two compression springs (413); The inner wall of outer shaft (411) is provided with only the bayonet (416) corresponding to pad (415), and the outer wall of inner shaft (412) is provided with multiple bayonets (416) corresponding to pad (415); The bayonet (416) is provided with a pop-up fixing device inside, corresponding to pad (415); The inner ring (433) of the damping ring (43) is fixedly connected with the connecting rod (42), and the outer wall is connected with the inner wall of outer ring (431) by elastic member (432); The elastic member (432) is annularly arranged multiple, and is fixed in the middle of damping ring (43).

2. The unmanned aerial vehicle with anti-collision structure according to claim 1, characterized in that: The second anti-collision device (5) includes: Frame (51), fixed on machine body (1); Universal joint (52), fixed in frame (51), and is elastically connected with the upper and lower inner walls of frame (51) by support spring (56); Connecting shaft (53), for telescopic structure, is fixedly connected with universal joint (52), and is located in the middle part of adjacent two first anti-collision devices (4); Supporting rod (54), V-shaped distribution, and the angle end is slidably fixed on connecting shaft (53) by circular ring (57); Anti-collision plate (55), arc surface, center and connecting shaft (53) protruding end fixed connection, both ends arc surface and the opening end of supporting rod (54) fixed connection, with both sides damping ring (43) there is certain safety interval.

3. The unmanned aerial vehicle with anti-collision structure according to claim 2, characterized in that: The circular ring (57) is fixedly connected with the angle end of the supporting rod (54), and is slidably connected with the outer wall of the connecting shaft (53).

4. The unmanned aerial vehicle with anti-collision structure according to claim 2, characterized in that: The anti-collision plate (55) is internally provided with a buffer spring, and externally provided with a wear-resistant plane.

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