CN218703879U

CN218703879U - Aircraft with protection device

Info

Publication number: CN218703879U
Application number: CN202223095260.0U
Authority: CN
Inventors: 胡华伟; 杨帆
Original assignee: Hunan Huifei Intelligent Technology Co ltd
Current assignee: Hunan Huifei Intelligent Technology Co ltd
Priority date: 2022-11-22
Filing date: 2022-11-22
Publication date: 2023-03-24
Anticipated expiration: 2032-11-22

Abstract

The utility model discloses an aircraft with a protection device, which comprises an aircraft body, wherein wings are arranged on the outer side of the aircraft body at equal intervals, a first anti-collision ring is detachably arranged on the outer side of each wing, a second anti-collision ring is detachably arranged above the first anti-collision ring, and a damping mechanism is arranged between the first anti-collision ring and the second anti-collision ring; through setting up first anticollision ring, the second anticollision ring, the installation pole, the piston piece, buffer spring, fastening bolt and L venturi tube, make the second anticollision ring receive the collision damage back, just can be convenient pull down the second anticollision ring through fastening bolt, then realize the purpose of changing the second anticollision ring on installing the installation pole on the L venturi tube with new second anticollision ring, thereby let the second anticollision ring be convenient for change after damaging, in order can not influence the normal flight of aircraft and reduce its time that can operate because of the damaged inconvenient change of second anticollision ring.

Description

Aircraft with protection device

Technical Field

The utility model relates to an aircraft technical field specifically is an aircraft with protection device.

Background

Unmanned aerial vehicle is safety device for aircraft indicates: an unmanned aircraft, referred to as "drone", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer. In the civil aspect, the unmanned aerial vehicle + the industry application is really just needed by the unmanned aerial vehicle; at present, the unmanned aerial vehicle is applied to the fields of aerial photography, agriculture, plant protection, miniature self-timer, express transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, romantic manufacturing and the like, the application of the unmanned aerial vehicle is greatly expanded, and developed countries actively expand the industrial application and develop the unmanned aerial vehicle technology;

present unmanned aerial vehicle often can appear because of the operation is not good in the in-process of using, the condition of collision appears in the in-process that leads to the flight of aircraft or descending to lead to unmanned aerial vehicle self the condition that damages to some unmanned aerial vehicles have installed the device that is used for carrying out the protection when flying unmanned aerial vehicle additional at present, though unmanned aerial vehicle has reduced the probability of damage when receiving the collision, but these protector receive the collision can appear damaging and the problem of inconvenient maintenance.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an aircraft with protection device to solve the problem mentioned in the above-mentioned background art.

In order to achieve the above object, the utility model provides a following technical scheme: the utility model provides an aircraft with protection device, includes the aircraft body, the wing is installed to equidistant in the outside of aircraft body, the outside detachable of wing is provided with first anticollision ring, the top detachable of first anticollision ring is provided with second anticollision ring, just be provided with damper between first anticollision ring and the second anticollision ring.

Preferably: the utility model discloses a wing, including first anticollision ring, first anticollision ring and wing, the junction of first anticollision ring and wing adopts the screw connection, equidistant a plurality of L venturi tube that is provided with in inboard of first anticollision ring, sliding connection has the piston piece in the inner chamber of L venturi tube, the top of piston piece is connected with the installation pole, the below of piston piece is provided with buffer spring, just buffer spring is located in the inner chamber of L venturi tube, equidistant a plurality of mounting hole that is equipped with in bottom of second anticollision ring, the upper end of installation pole is run through the roof and the inside of cartridge to the mounting hole of L venturi tube, install on the lateral wall of mounting hole and be used for the location the fastening bolt of installation pole position.

Preferably: the wing includes mounting bracket, paddle and motor, several the equidistant setting of mounting bracket is in on the outer periphery of aircraft body, the motor sets up keep away from on the mounting bracket one of aircraft body is served, the paddle with transmission connection between the main shaft of motor.

Preferably: and a plurality of lifting feet made of soft materials are arranged at the bottom of the first anti-collision ring at equal intervals.

Preferably: the outer diameter of the first anti-collision ring is larger than that of the second anti-collision ring.

Preferably: the first anti-collision ring and the second anti-collision ring are made of soft materials.

Preferably: the distance between the first and second impact rings is greater than the thickness of the aircraft body.

Compared with the prior art, the beneficial effects of the utility model are that:

the utility model provides a pair of aircraft with protection device, through setting up first anticollision ring, the second anticollision ring, the installation pole, the piston piece, buffer spring, fastening bolt and L venturi tube, make the second anticollision ring receive the collision damage back, just can be convenient pull down the second anticollision ring through fastening bolt, then realize the purpose of changing the second anticollision ring on installing the pole to the L venturi tube with new second anticollision ring, thereby let the second anticollision ring be convenient for change after damaging, in order can not influence the normal flight of aircraft and subtract the time that can work because of the damaged inconvenient change of second anticollision ring.

Drawings

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

FIG. 2 is an enlarged view of the point A of FIG. 1 according to the present invention;

fig. 3 is a top view of the wing of the present invention.

In the figure: the aircraft comprises an aircraft body 1, wings 2, a mounting rack 21, blades 22, a motor 23, a first anti-collision ring 3, a second anti-collision ring 4, an L-shaped pipe 5, a piston block 6, a mounting rod 7, a buffer spring 8, a mounting hole 9, a fastening bolt 10 and a lifting foot 11.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Referring to fig. 1-3, the present invention provides a technical solution: an aircraft with a protection device comprises an aircraft body 1, wherein a plurality of wings 2 are arranged on the outer side of the aircraft body 1 at equal intervals, each wing 2 comprises a mounting frame 21, a paddle 22 and a motor 23, the mounting frames 21 are arranged on the outer circumferential surface of the aircraft body 1 at equal intervals, the motor 23 is arranged at one end, far away from the aircraft body 1, of the mounting frame 21, the paddles 22 are in transmission connection with a main shaft of the motor 23, a first anti-collision ring 3 is arranged on the outer side of the wings 2, and the connection part of the first anti-collision ring 3 and the wings 2 is connected through screws, so that when the first anti-collision ring 3 is damaged, the replacement operation of the first anti-collision ring 3 can be conveniently realized through dismounting the screws;

the bottom of the first anti-collision ring 3 is provided with a plurality of lifting feet 11 at equal intervals, the lifting feet 11 are made of soft materials so as to reduce the influence of vibration generated when the unmanned aerial vehicle descends on the unmanned aerial vehicle, the second anti-collision ring 4 is detachably arranged above the first anti-collision ring 3, the outer diameter of the first anti-collision ring 3 is larger than that of the second anti-collision ring 4, the first anti-collision ring 3 and the second anti-collision ring 4 are both made of soft materials, the distance between the first anti-collision ring 3 and the second anti-collision ring 4 is larger than the thickness of the aircraft body 1, the inner side of the first anti-collision ring 3 is provided with a plurality of L-shaped pipes 5 at equal intervals, piston blocks 6 are slidably connected in the inner cavities of the L-shaped pipes 5, the upper parts of the piston blocks 6 are connected with mounting rods 7, buffer springs 8 are arranged below the piston blocks 6 and also arranged in the inner cavities of the L-shaped pipes 5, mounting holes 9 are formed in the bottom of the second anti-collision ring 4 at equal intervals, the mounting rods 7 penetrate through the top wall of the L-shaped pipes 5 and are fastened to the side walls of the mounting holes 9, and bolts 10 used for positioning the mounting rods are installed on the mounting holes.

The working principle is as follows: when the aircraft collides, when first anticollision ring 3 and second anticollision ring 4 received the effort when colliding, second anticollision ring 4 can play the effect of buffering through buffer spring 8 on installation pole 7 bottom piston block 6, thereby can reduce the degree that second anticollision ring 4 appears damaging, if second anticollision ring 4 damages when the degree that needs to be changed, just can be through not hard up fastening bolt 10, convenient pull down second anticollision ring 4 from first anticollision ring 3 and in time change again, consequently can not influence the normal flight of aircraft and subtract the time that its can be worked.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. An aircraft with a protection device, comprising an aircraft body (1), characterized in that: wings (2) are installed at the outer side of the aircraft body (1) at equal intervals, a first anti-collision ring (3) is detachably arranged on the outer side of the wings (2), a second anti-collision ring (4) is detachably arranged above the first anti-collision ring (3), and a damping mechanism is arranged between the first anti-collision ring (3) and the second anti-collision ring (4).

2. An aircraft with a protection device according to claim 1, characterized in that: the utility model discloses a wing, including first anticollision ring (3), wing (2), mounting rod (7), buffer spring (8) are provided with in the below of piston piece (6), just buffer spring (8) are located in the inner chamber of L venturi tube (5), sliding connection has piston block (6) in the inboard equidistant of first anticollision ring (3), the top of piston block (6) is connected with mounting rod (7), the top of piston block (6) is provided with buffer spring (8), just buffer spring (8) are located in the inner chamber of L venturi tube (5), the bottom equidistant of second anticollision ring (4) is equipped with a plurality of mounting hole (9), the upper end of mounting rod (7) is run through the roof of L venturi tube (5) and the inside of cartridge to mounting hole (9), install on the lateral wall of mounting hole (9) and be used for the location fastening bolt (10) of mounting rod (7) position.

3. An aircraft with a protection device according to claim 1, characterized in that: wing (2) include mounting bracket (21), paddle (22) and motor (23), several equidistant setting of mounting bracket (21) is in on the outer periphery of aircraft body (1), motor (23) set up keep away from on mounting bracket (21) one of aircraft body (1) is served, paddle (22) with the transmission is connected between the main shaft of motor (23).

4. An aircraft with a protection device according to claim 3, characterized in that: the bottom of the first anti-collision ring (3) is provided with a plurality of lifting feet (11) made of soft materials at equal intervals.

5. An aircraft with a protection device according to claim 1, characterized in that: the outer diameter of the first anti-collision ring (3) is larger than that of the second anti-collision ring (4).

6. An aircraft with a protection device according to claim 5, characterized in that: the first anti-collision ring (3) and the second anti-collision ring (4) are both made of soft materials.

7. An aircraft with a protection device according to claim 6, characterized in that: the distance between the first anti-collision ring (3) and the second anti-collision ring (4) is larger than the thickness of the aircraft body (1).