CN216424730U

CN216424730U - Rotor unmanned aerial vehicle shock attenuation undercarriage

Info

Publication number: CN216424730U
Application number: CN202121908517.2U
Authority: CN
Inventors: 张立; 艾剑良
Original assignee: Fudan University
Current assignee: Fudan University
Priority date: 2021-08-13
Filing date: 2021-08-13
Publication date: 2022-05-03
Anticipated expiration: 2031-08-13

Abstract

The utility model discloses a shock-absorbing undercarriage of a rotor wing unmanned aerial vehicle, which belongs to the field of unmanned aerial vehicles and comprises a fixed plate, an underframe and a plurality of supporting rods connected between the fixed plate and the underframe, wherein two ends of each supporting rod are respectively hinged with a fixed block and a sliding block; the chassis comprises a frame body and a damping assembly arranged on the frame body, and each sliding block is provided with the damping assembly; the damping assembly comprises a piston cylinder, a piston rod, a spring and a spring baffle plate, the piston cylinder is fixedly installed on the frame body, the piston is located in the piston cylinder, one end of the piston rod is fixedly connected to the piston, the other end of the piston rod extends out of the piston cylinder and then is fixedly connected with the sliding block, the spring baffle plate is sleeved on the side wall of the piston rod located on the outer side of the piston cylinder, the spring baffle plate is fixed on the frame body, and the spring is sleeved on the side wall of the piston rod located between the spring baffle plate and the sliding block. The utility model has better shock absorption effect and can effectively reduce the impact of the unmanned aerial vehicle during landing.

Description

Rotor unmanned aerial vehicle shock attenuation undercarriage

Technical Field

The utility model relates to the field of unmanned aerial vehicles, in particular to a damping undercarriage of a rotor unmanned aerial vehicle.

Background

Unmanned aerial vehicle is unmanned aerial vehicle for short, is the unmanned vehicles who utilizes radio remote control equipment and self-contained program control device to control, and unmanned aerial vehicle is the general name of unmanned aerial vehicle in fact, can divide into from the technical perspective: compared with manned aircrafts, the unmanned fixed wing aircraft, the unmanned vertical take-off and landing aircraft, the unmanned airship, the unmanned helicopter, the unmanned multi-rotor aircraft, the unmanned umbrella wing aircraft and the like have the advantages of small volume, low manufacturing cost, convenient use, low requirement on the battlefield environment, strong battlefield viability and the like. Since the unmanned aircraft has important significance for future air battles, the research and development work of the unmanned aircraft is carried out in all major military countries in the world. In addition, the unmanned aerial vehicle has wide application and has better development prospect in the industries of police, city management, agriculture, geology, meteorology, electric power, emergency rescue and disaster relief, video shooting and the like.

The landing gear is a device which is used for supporting the gravity of the airplane and bearing corresponding loads when the unmanned aerial vehicle parks, slides, takes off, lands and runs on the ground, and when the unmanned aerial vehicle lands, the landing gear lands firstly, and the landing gear can consume and absorb the impact energy of the airplane during landing. The big shock attenuation effect of unmanned aerial vehicle undercarriage on the present market is not good, can't effectively alleviate the collision impact force of unmanned aerial vehicle and ground, and unstable when leading to unmanned aerial vehicle to descend receives great impact easily, and the inside comparatively accurate instrument, the equipment of needing to be equipped with usually of unmanned aerial vehicle, and stronger impact will be to the precision that reduces instrument and equipment, and all sides performance of unmanned aerial vehicle consequently receives the influence.

SUMMERY OF THE UTILITY MODEL

Aiming at the problem that the damping capacity of the landing gear of the unmanned aerial vehicle is poor in the prior art, the utility model aims to provide the damping landing gear of the rotor unmanned aerial vehicle.

In order to achieve the purpose, the technical scheme of the utility model is as follows:

a shock absorption undercarriage of a rotor wing unmanned aerial vehicle comprises a fixed plate, an underframe and a plurality of supporting rods connected between the fixed plate and the underframe, wherein two ends of each supporting rod are respectively hinged with a fixed block and a sliding block; the chassis comprises a frame body and a damping assembly arranged on the frame body, wherein each sliding block is provided with the damping assembly; the damping assembly comprises a piston cylinder, a piston rod, a spring and a spring baffle plate, the piston cylinder is fixedly arranged on the frame body, the piston is positioned in the piston cylinder, one end of the piston rod is fixedly connected to the piston, the other end of the piston rod extends out of the piston cylinder and then is fixedly connected with the sliding block, the spring baffle plate is sleeved on the side wall of the piston rod positioned on the outer side of the piston cylinder, the spring baffle plate is fixed on the frame body, and the spring is sleeved on the side wall of the piston rod positioned between the spring baffle plate and the sliding block;

gaps for air inlet and outlet are arranged between the piston and the piston cylinder and between the piston rod and the piston cylinder; or the piston and the piston cylinder and the piston rod and the piston cylinder are in sealing fit, and damping air holes for air inlet and outlet are formed in the two ends of the piston cylinder.

Preferably, the support rods are uniformly arranged in the circumferential direction.

Preferably, the number of the support rods is two, the support body is of a long strip-shaped structure, open grooves penetrating through two ends of the support body in the length direction are formed in the support body, the sliding blocks connected with the two support rods are located in the open grooves, and the piston cylinders are fixedly installed at two ends of the support body in the length direction.

Furthermore, the underframe also comprises a sponge shock-absorbing layer laid on the surface of the frame body.

By adopting the technical scheme, the utility model has the beneficial effects that:

1. due to the arrangement of the sliding block, the spring and the spring baffle, the body of the unmanned aerial vehicle presses the fixed plate downwards when the unmanned aerial vehicle lands, and after the sliding block is driven to slide by the supporting rod, the spring can provide resistance for preventing the sliding block from sliding, so that the descending amplitude of the body is reduced, and the impact force is reduced;

2. and because the piston cylinder, the piston and the piston rod are arranged, the piston can be synchronously driven to move in the piston cylinder when the sliding block moves, and because the piston cylinder is a closed space, air cannot be continuously compressed after being compressed to a certain degree, so that reaction force is formed to prevent the sliding block from moving, and the purposes of reducing the descending amplitude of the machine body and reducing the impact force are also achieved.

Drawings

FIG. 1 is a schematic structural view of the present invention;

fig. 2 is a partially enlarged view of a portion a in fig. 1.

In the figure, 1-a fixing plate, 2-an underframe, 3-a supporting rod, 4-a fixing block, 5-a sliding block, 20-a frame body, 21-a piston cylinder, 22-a piston, 23-a piston rod, 24-a spring, 25-a spring baffle, 26-an open slot and 27-a sponge shock-absorbing layer.

Detailed Description

The following further describes embodiments of the present invention with reference to the drawings. It should be noted that the description of the embodiments is provided to help understanding of the present invention, but the present invention is not limited thereto. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.

It should be noted that in the description of the present invention, the terms "upper", "lower", "left", "right", "front", "rear", and the like indicate orientations or positional relationships based on structures shown in the drawings, and are only used for convenience in describing the present invention, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.

In the technical scheme, the terms "first" and "second" are only used for referring to the same or similar structures or corresponding structures with similar functions, and are not used for ranking the importance of the structures, or comparing the sizes or other meanings.

In addition, unless expressly stated or limited otherwise, the terms "mounted" and "connected" are to be construed broadly, e.g., the connection may be a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; the two structures can be directly connected or indirectly connected through an intermediate medium, and the two structures can be communicated with each other. To those skilled in the art, the specific meanings of the above terms in the present invention can be understood in light of the present general concepts, in connection with the specific context of the scheme.

Example one

The utility model provides a rotor unmanned aerial vehicle shock attenuation undercarriage, as shown in figure 1 and figure 2, includes fixed plate 1, chassis 2 and connects a plurality of bracing pieces 3 between fixed plate 1 and chassis 2. The fixed plate 1 is of a plate-shaped structure, and the top surface of the fixed plate is used for mounting a body of the unmanned aerial vehicle; chassis 2 is located fixed plate 1 under, and chassis 2 is used for supporting subaerial when unmanned aerial vehicle descends.

Wherein, the upper and lower both ends of bracing piece 3 are articulated respectively to have fixed block 4 and slider 5, and fixed block 4 fixed connection is on the bottom surface of fixed plate 1, and slider 5 is connected on the top surface of chassis 2 then slidable. In this embodiment, the fixed block 4 and the sliding block 5 are respectively fixed with a pivot, and two ends of the supporting rod 3 are respectively provided with a shaft hole matched with the pivot, so as to realize the hinged connection.

Wherein, the chassis 2 includes a frame body 20 and a shock absorption assembly disposed on the frame body 20, and the sliding block 5 can slide on the frame body 20 through a sliding slot or other similar structures. Wherein, each slide block 5 is provided with a damping component, and the slide block 5 is damped by the damping component.

In the present embodiment, the shock absorbing assembly is configured to include a piston cylinder 21, a piston 22, a piston rod 23, a spring 24, and a spring damper 25. The piston cylinder 21 is fixedly mounted on the frame body 20, the piston 22 is located in the piston cylinder 21 and is axially movable, one end of the piston rod 23 is fixedly connected to one end surface of the piston 22, and the other end of the piston rod 23 extends out of the piston cylinder 21 and is fixedly connected with the corresponding slide block 5. The spring baffle 25 is annular and is sleeved on the side wall of the piston rod 23 positioned outside the piston cylinder 21, and meanwhile, the spring baffle 25 is fixed on the frame body 20; and the spring 24 is sleeved on the side wall of the piston rod 23 between the spring baffle 25 and the sliding block 5.

With the arrangement, when the damping undercarriage is installed on an unmanned aerial vehicle for use, after the unmanned aerial vehicle falls, the chassis 2 firstly contacts the ground, then the body of the unmanned aerial vehicle continuously falls and presses gravity on the supporting rod 3 through the fixing plate 1, the lower end of the supporting rod 3 pushes the sliding block 5 to slide on the chassis 2, the sliding block 5 compresses the spring 24 on one hand and pushes the piston 22 on the other hand, so that the sliding of the sliding block 5 is hindered by the elastic force given by the spring 24 and the pressure given by air in the piston cylinder 21, the falling amplitude of the body of the unmanned aerial vehicle is reduced, and the purpose of relieving impact is achieved.

Wherein, foretell bracing piece 3 is generally configured with a plurality ofly, and a plurality of 3 circumference of bracing piece evenly arrange so that each side of unmanned aerial vehicle evenly receives the force. In the present embodiment, two support rods 3 are specifically configured, and the two support rods 3 are symmetrically arranged in the left-right direction. Correspondingly, the frame body 20 is configured to be a long strip structure, in addition, the frame body 20 is provided with an open slot 26 penetrating through two ends of the frame body 20 in the length direction, and the sliding blocks 5 connected with the two support rods 3 are both positioned in the open slot 26; the piston cylinder 21 is fixedly installed at both ends of the frame body 20 in the length direction, and the axes of the piston cylinder 21 and the open slot 26 are overlapped, so that the piston rod 23 can extend into the open slot 26 to be connected with the slider 5, and in addition, the spring baffle 25 in the damping assembly is fixedly installed in the open slot 26.

So set up, when reducing bracing piece 3 quantity, can also accomodate most parts in damper in the inside of support body 20 so that protect.

In the present embodiment, gaps for air intake and exhaust are provided between the piston 22 and the piston cylinder 21 and between the piston rod 23 and the piston cylinder 21. So set up for when slider 5 passes through piston rod 23 drive piston 22 and moves in piston cylinder 21, the air in the piston cylinder 21 can exchange through clearance and atmosphere, thereby avoid the air in the piston cylinder 21 just can not compress after receiving certain pressure, and then lead to slider 5 very fast just unmovable shortcoming, thereby improved slider 5's motion stroke, can effectively postpone the time of action of resistance, reduce instantaneous impact force.

Or similarly, in another embodiment, damping air holes for air to enter and exit can be arranged at both ends of the piston cylinder 21 under the condition that the piston 22 and the piston cylinder 21 are in sealing fit and the piston rod 23 and the piston cylinder 21 are in sealing fit. The piston cylinder 21 can be communicated with the atmosphere through the damping air holes, and the effects of improving the motion stroke of the slide block 5, delaying the action time of resistance and reducing the instantaneous impact force are also achieved.

Example two

It differs from the above embodiment in that: in this embodiment, the chassis 2 further includes a sponge shock-absorbing layer 27 laid on the surface of the frame body 20, and the sponge shock-absorbing layer is laid at least on the bottom surface side of the frame body 21 contacting with the ground, preferably, the frame body 21 is wrapped in an all-directional manner.

The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the described embodiments. It will be apparent to those skilled in the art that various changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the utility model, and the scope of protection is still within the scope of the utility model.

Claims

1. The utility model provides a rotor unmanned aerial vehicle shock attenuation undercarriage which characterized in that: the supporting device comprises a fixing plate, an underframe and a plurality of supporting rods connected between the fixing plate and the underframe, wherein two ends of each supporting rod are respectively hinged with a fixing block and a sliding block, the fixing blocks are fixedly connected to the fixing plate, and the sliding blocks are slidably connected to the underframe; the chassis comprises a frame body and a damping assembly arranged on the frame body, wherein each sliding block is provided with the damping assembly; the damping assembly comprises a piston cylinder, a piston rod, a spring and a spring baffle plate, the piston cylinder is fixedly arranged on the frame body, the piston is positioned in the piston cylinder, one end of the piston rod is fixedly connected to the piston, the other end of the piston rod extends out of the piston cylinder and then is fixedly connected with the sliding block, the spring baffle plate is sleeved on the side wall of the piston rod positioned on the outer side of the piston cylinder, the spring baffle plate is fixed on the frame body, and the spring is sleeved on the side wall of the piston rod positioned between the spring baffle plate and the sliding block;

2. The rotorcraft shock absorbing landing gear of claim 1, wherein: the bracing piece has a plurality ofly and circumference evenly arranged.

3. The rotorcraft shock absorbing landing gear of claim 1, wherein: the support body is of a long strip-shaped structure, open grooves penetrating through two ends of the support body in the length direction are formed in the support body, the sliding blocks connected with the support rods are located in the open grooves, and the piston cylinders are fixedly installed at two ends of the support body in the length direction.

4. A rotorcraft shock absorbing landing gear according to any one of claims 1 to 3, wherein: the underframe also comprises a sponge shock-absorbing layer laid on the surface of the frame body.