Low-altitude aircraft with buffer undercarriage

Abstract

The utility model discloses a low-altitude aircraft with a buffer undercarriage, and relates to the technical field of low-altitude aircrafts. The unmanned aerial vehicle comprises a flying assembly and an auxiliary assembly, the flying assembly comprises two rectangular protruding blocks, the auxiliary assembly comprises four supporting side plates, and the four supporting side plates are arranged on the left sides and the right sides of the two rectangular protruding blocks respectively. Through the auxiliary assembly, specifically clockwise rotation of the right transmission gear, and transmission connection between the two transmission gears, the left transmission gear can rotate anticlockwise, so that the left supporting side plate and the right supporting side plate rotate in the direction close to each other, and therefore rotation of the supporting side plates can be controlled through rotation of the transmission gears; and when the supporting side plates move in the direction close to each other, the supporting side plates can turn over downwards to provide additional support for the rectangular convex blocks, so that the unmanned aerial vehicle is prevented from toppling over during landing, and the unmanned aerial vehicle is prevented from being damaged due to toppling over.

Description

TECHNICAL FIELD

[0001] The utility model belongs to low altitude aircraft technical field, in particular, relate to a low altitude aircraft with buffer landing gear. BACKGROUND

[0002] Low altitude aircraft refers to the ground to 1000 meters below the airspace operation of a kind of aircraft, usually including unmanned aerial vehicle, helicopter, light aircraft and emerging electric vertical take-off and landing aircraft, etc., relying on new energy, intelligent navigation and light weight material technology, this kind of aircraft has short take-off and landing, flexible maneuvering and low noise characteristics, can be widely used in logistics distribution, emergency rescue, agricultural plant protection, geographic mapping and urban air traffic, etc.

[0003] Unmanned aerial vehicle is a common low altitude aircraft, the unmanned aerial vehicle usually uses landing gear to land when landing, but the bottom of the landing gear of the unmanned aerial vehicle is usually a long rod, which makes the contact area of the landing gear with the ground smaller, causing the unmanned aerial vehicle to tip over when landing, and thus causing the unmanned aerial vehicle to be damaged, therefore we propose a low altitude aircraft with buffer landing gear. UTILITY MODEL CONTENT

[0004] The utility model discloses a low altitude aircraft with buffer landing gear, through auxiliary assembly, specifically clockwise rotating right side transmission gear, through the transmission connection between two transmission gears, will make left side transmission gear counterclockwise rotation, make the support side plate of left side and right side rotate to the direction of mutual approach, so can control the rotation of support side plate through the rotation of transmission gear, when support side plate moves to the direction of mutual approach, will provide additional support for rectangular boss by turning down, prevent unmanned aerial vehicle from tipping over when landing, avoid unmanned aerial vehicle from being damaged due to tipping over, solve the existing unmanned aerial vehicle usually uses landing gear to land when landing, but the bottom of the landing gear of the unmanned aerial vehicle is usually a long rod, which makes the contact area of the landing gear with the ground smaller, causing the unmanned aerial vehicle to tip over when landing, and thus causing the unmanned aerial vehicle to be damaged.

[0005] To solve the above technical problems, the utility model is realized by the following technical schemes:

[0006] The utility model discloses a low altitude aircraft with buffer landing gear, including flight subassembly and auxiliary assembly, flight subassembly includes two rectangular bosses, auxiliary assembly includes four support side plates, four support side plates set up respectively in two rectangular bosses left side and right side, two support side plates are with rectangular boss as center mirror image setting, support side plate front and back are all rotationally connected with limit ring, two limit rings located left side and two limit rings located right side mutually close one side all with rectangular boss outer surface fixed connection, limit ring is fixed connection with rectangular boss, support side plate front center place fixed connection has transmission gear, transmission gear located left side and transmission gear located right side meshing connection, through setting the meshing connection between two transmission gears, makes two transmission gears can drive support side plate to rotate to opposite direction.

[0007] Further, the rectangular boss top is provided with three dampers, the rectangular boss top is provided with rectangular top plate, the damper top is fixedly connected with the rectangular top plate, the damper outer surface is sleeved with telescopic spring, the telescopic spring top is fixedly connected with the rectangular top plate, the telescopic spring bottom is fixedly connected with the rectangular boss, by setting the damper, the damper can absorb the impact generated by sliding, and by setting the telescopic spring, the damper can be driven to rebound and reset, guaranteeing the subsequent work.

[0008] Further, three dampers are horizontally arrayed with the top of the rectangular boss as the center, and the bottoms of the three dampers are fixedly connected with the top of the rectangular boss.

[0009] Further, the top center of the rectangular top plate is fixedly connected with an aircraft body, and the front and back of the aircraft body are fixedly connected with a plurality of connecting rings, and the plurality of connecting rings are horizontally arrayed with the aircraft body as the center.

[0010] Furthermore, a circular protrusion is fixedly connected to the back of the supporting side plate. The circular protrusion contacts the back of the limiting ring located on the rear side, and the front of the limiting ring located on the front side contacts the back of the transmission gear. Gear outer boxes are fitted onto the outer surfaces of the two transmission gears. The back of the gear outer box is fixedly connected to the front of the rectangular protrusion. The front of both transmission gears penetrates through the gear outer box and extends outward. The front of the transmission gear is rotatably connected to the gear outer box through the penetration point. A motor is provided on the front of the right transmission gear. The back of the motor is fixedly connected to the gear outer box. The front of the right transmission gear 24 is fixedly connected to the output end of the motor 26. By providing the motor, the motor can control the rotation of the transmission gear through the output end. By providing the gear outer box, the transmission gear can be protected to prevent foreign objects from entering the gap between the two transmission gears and causing the transmission gear to jam.

[0011] This utility model has the following beneficial effects:

[0012] 1. This utility model uses an auxiliary component, specifically, to rotate the right transmission gear clockwise. Through the transmission connection between the two transmission gears, the left transmission gear rotates counterclockwise, causing the left and right support side plates to rotate towards each other. In this way, the rotation of the support side plates can be controlled by the rotation of the transmission gears. When the support side plates move towards each other, they will flip downwards to provide additional support for the rectangular protrusion, preventing the drone from tipping over during landing and avoiding damage to the drone due to tipping.

[0013] 2. This utility model sets up a flight component, specifically a rectangular protrusion that moves downward. When the rectangular protrusion contacts the ground, it slides upward along the damper and compresses the telescopic spring. In this way, the vibration generated when the rectangular protrusion contacts the ground can be eliminated by the sliding between the rectangular protrusion and the damper, so that the drone can land smoothly and avoid damage caused by the vibration during landing.

[0014] Of course, any product implementing this utility model does not necessarily need to achieve all of the advantages described above at the same time. Attached Figure Description

[0015] To more clearly illustrate the technical solutions of the embodiments of this utility model, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0017] Figure 2 It is the schematic diagram of aircraft body structure of the utility model;

[0018] Figure 3 It is the schematic diagram of support side plate section of the utility model;

[0019] Figure 4 It is the schematic diagram of rectangular protruding block section of the utility model;

[0020] Figure 5 It is the schematic diagram of gear outer box section of the utility model.

[0021] In the drawings, the component list represented by each sign is as follows:

[0022] 1, flight assembly; 111, aircraft body; 112, connecting ring; 12, rectangular top plate; 13, damper; 14, telescopic spring; 15, rectangular protruding block; 2, auxiliary assembly; 21, support side plate; 22, limiting ring; 23, circular protruding block; 24, transmission gear; 25, gear outer box; 26, motor. DETAILED DESCRIPTION

[0023] The technical scheme in the embodiments of the utility model will be described clearly and completely below with reference to the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the utility model.

[0024] Please refer to Figures 1-5As shown, the utility model is a kind of low altitude aircraft with buffer landing gear, including flight component 1 and auxiliary assembly 2, flight component 1 includes two rectangular bosses 15, auxiliary assembly 2 includes four support side plates 21, four support side plates 21 are respectively arranged in the left side and right side of two rectangular bosses 15, two support side plates 21 are mirror image with rectangular boss 15 as center, support side plate 21 front and back are rotatably connected with limiting ring 22, the side of the two limiting rings 22 located on the left and the two limiting rings 22 located on the right are close to each other with the outer surface of rectangular boss 15 fixedly connected, limiting ring 22 is fixedly connected with rectangular boss 15, the center of support side plate 21 front is fixedly connected with transmission gear 24, the transmission gear 24 located on the left is engaged with the transmission gear 24 located on the right, through auxiliary assembly 2, specifically clockwise rotating right side transmission gear 24, through the transmission connection between two transmission gears 24, left side transmission gear 24 will rotate counterclockwise, make left side and right side support side plate 21 rotate to the direction of mutual approach, so it can control the rotation of support side plate 21 by the rotation of transmission gear 24, when support side plate 21 moves to the direction of mutual approach, it will be turned down to provide additional support for rectangular boss 15, prevent unmanned aerial vehicle from toppling when landing, avoid unmanned aerial vehicle from being damaged due to toppling, rectangular boss 15 top is provided with three dampers 13, rectangular boss 15 top is provided with rectangular top plate 12, damper 13 top is fixedly connected with rectangular top plate 12, damper 13 outer surface is provided with telescopic spring 14, telescopic spring 14 top is fixedly connected with rectangular top plate 12, telescopic spring 14 bottom is fixedly connected with rectangular boss 15, by setting flight component 1, specifically, rectangular boss 15 is moved downward, when rectangular boss 15 contacts ground, rectangular boss 15 will slide upward along damper 13, and compresses telescopic spring 14, so it can eliminate the vibration generated when rectangular boss 15 contacts ground by the sliding between rectangular boss 15 and damper 13, so that unmanned aerial vehicle can land smoothly, avoid unmanned aerial vehicle from being damaged due to toppling caused by landing vibration, three dampers 13 are horizontally arrayed with the top of rectangular boss 15 as center, the bottom of three dampers 13 is fixedly connected with the top of rectangular boss 15, the top center of rectangular top plate 12 is fixedly connected with aircraft body 111, the front and back of aircraft body 111 are fixedly connected with a plurality of connecting rings 112, a plurality of connecting rings 112 are horizontally arrayed with aircraft body 111 as center, the back of support side plate 21 is fixedly connected with circular boss 23, circular boss 23 contacts the back of limiting ring 22 located on rear side, the front of limiting ring 22 located on front side contacts the back of transmission gear 24, the outer surface of two transmission gears 24 is provided with gear outer box 25, the back of gear outer box 25 is fixedly connected with the front of rectangular boss 15, the front of two transmission gears 24 all penetrates gear outer box 25 and extends outward,The front surface of the transmission gear 24 is rotationally connected with the gear outer box 25, the front surface of the transmission gear 24 on the right side is provided with the motor 26, the back surface of the motor 26 is fixedly connected with the gear outer box 25, and the front surface of the transmission gear 24 on the right side is fixedly connected with the output end of the motor 26.

[0025] One specific application of the embodiment is that when the aircraft body 111 is ready to land, the motor 26 is started, the output end of the motor 26 drives the transmission gear 24 connected therewith to rotate through the shaft coupling, and the transmission gear 24 away from the motor 26 rotates in the opposite direction through the meshing connection between the two transmission gears 24, so that the support side plates 21 arranged on the left side and the right side of the rectangular protrusion 15 are all rotated to the bottom of the rectangular protrusion 15, and the rotation of the support side plates 21 to the bottom assists the rectangular protrusion 15, thereby improving the supporting force of the equipment.

[0026] Then, the aircraft body 111 after the support side plates 21 are deployed is controlled to move downward, so that the rectangular protrusion 15 and the bottom of the support side plates 21 are in contact with the ground, and when the rectangular protrusion 15 is in contact with the ground, the impact force generated when the aircraft body 111 lands is absorbed by the damper 13.

[0027] In the description of the present specification, the description of the terms "one embodiment", "example", "specific example" and the like means that the specific features, structures, materials or characteristics described in connection with the embodiment or example are contained in at least one embodiment or example of the present application. In the present specification, the illustrative description of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0028] The preferred embodiments of the application disclosed above are only used to help explain the application. The preferred embodiments do not describe all the details, nor limit the application to the specific embodiments described. Obviously, according to the content of the present specification, many modifications and changes can be made. The present specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the application, so that those skilled in the art can well understand and utilize the application. The application is limited by the claims and their entire scope and equivalents.

Claims

1. A low altitude vehicle with a cushioned landing gear, characterized by: Including flight assembly (1) and auxiliary assembly (2), the flight assembly (1) includes two rectangular protrusions (15), the auxiliary assembly (2) includes four support side plates (21), four the support side plates (21) are respectively arranged on the left side and the right side of two rectangular protrusions (15), two the support side plates (21) are mirror image arranged with rectangular protrusion (15) as center, the front and back of support side plate (21) are rotatably connected with limit ring (22), the side of two the limit ring (22) located on the left side and the side of two limit ring (22) located on the right side are fixedly connected with the outer surface of rectangular protrusion (15), the limit ring (22) is fixedly connected with rectangular protrusion (15), the front center of support side plate (21) is fixedly connected with transmission gear (24), the transmission gear (24) located on the left side is engagedly connected with the transmission gear (24) located on the right side.

2. A low altitude vehicle with a cushioned undercarriage according to claim 1, characterized in that, The top of the rectangular protrusion (15) is provided with three dampers (13), the top of the rectangular protrusion (15) is provided with a rectangular top plate (12), the top of the damper (13) is fixedly connected with the rectangular top plate (12), the outer surface of the damper (13) is sleeved with a telescopic spring (14), the top of the telescopic spring (14) is fixedly connected with the rectangular top plate (12), and the bottom of the telescopic spring (14) is fixedly connected with the rectangular protrusion (15).

3. A low altitude vehicle with a cushioned undercarriage according to claim 2, characterized in that, Three the dampers (13) are horizontally arrayed with the top of rectangular protrusion (15) as center, and the bottoms of three the dampers (13) are fixedly connected with the top of rectangular protrusion (15).

4. The low altitude vehicle with a cushioned landing gear according to claim 2, characterized in that, The top center of the rectangular top plate (12) is fixedly connected with an aircraft body (111), the front and back of the aircraft body (111) are fixedly connected with a plurality of connecting rings (112), and a plurality of the connecting rings (112) are horizontally arrayed with the aircraft body (111) as center.

5. The low altitude vehicle with a cushioned landing gear according to claim 1, wherein, The back of the support side plate (21) is fixedly connected with a circular protrusion (23), the back of the circular protrusion (23) is in contact with the back of the limit ring (22) located on the rear side, and the front of the limit ring (22) located on the front side is in contact with the back of the transmission gear (24).

6. A low altitude vehicle with a cushioned undercarriage according to claim 5, characterized in that, The outer surfaces of two the transmission gears (24) are sleeved with a gear outer box (25), the back of the gear outer box (25) is fixedly connected with the front of the rectangular protrusion (15), the front of two the transmission gears (24) penetrates the gear outer box (25) and extends outward, and the front of the transmission gear (24) is rotatably connected with the gear outer box (25) penetrated.

7. A low altitude vehicle with a cushioned undercarriage according to claim 6, characterized in that, The front of the transmission gear (24) located on the right side is provided with an electric motor (26), the back of the electric motor (26) is fixedly connected with the gear outer box (25), and the front of the transmission gear (24) located on the right side is fixedly connected with the output end of the electric motor (26).

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