CN214776611U

CN214776611U - Radome buffer type unmanned aerial vehicle

Info

Publication number: CN214776611U
Application number: CN202120755517.7U
Authority: CN
Inventors: 朱进
Original assignee: Jiangsu Yidian Aviation Technology Co ltd
Current assignee: Jiangsu Yidian Aviation Technology Co ltd
Priority date: 2021-04-12
Filing date: 2021-04-12
Publication date: 2021-11-19
Anticipated expiration: 2031-04-12

Abstract

The utility model discloses a radome buffering formula unmanned aerial vehicle, including the unmanned aerial vehicle body, unmanned aerial vehicle body bottom surface is provided with a plurality of mounting panels, and the mounting panel is connected with unmanned aerial vehicle body bottom surface through a plurality of installation screw rods, and the mounting panel bottom surface has set firmly the buffering intubate perpendicularly, and it has the buffering inserted bar to peg graft in the buffering intubate, buffering inserted bar lower extreme and buffer board rigid coupling, and the cover is equipped with buffer spring on the buffering inserted bar, buffer spring top and buffering intubate rigid coupling, buffer spring lower extreme and buffer board rigid coupling, and the buffer board bottom surface has set firmly the gasbag. When unmanned aerial vehicle landed, the gasbag can effectively play the cushioning effect, and when unmanned aerial vehicle landed, the buffering inserted bar made buffer spring compressed in inserting the buffering inserted tube, impact force when can effectively mitigateing the landing, prevented that unmanned aerial vehicle from damaging to when unmanned aerial vehicle falls because of the accident out of control, break away from with the fixed column through the flexible end of controlling miniature electric telescopic handle, can make the canvas rise and expand, delay unmanned aerial vehicle's falling speed.

Description

Radome buffer type unmanned aerial vehicle

Technical Field

The utility model relates to an unmanned aerial vehicle field especially relates to a radome buffer type unmanned aerial vehicle.

Background

An unmanned aircraft, abbreviated as "drone", and abbreviated in english as "UAV", 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.

Drones tend to be more suitable for tasks that are too "fool, dirty, or dangerous" than are manned aircraft. Unmanned aerial vehicles can be classified into military and civil applications according to the application field. For military use, unmanned aerial vehicles divide into reconnaissance aircraft and target drone. 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 industrial application and develop unmanned aerial vehicle technology.

At present, a slow landing device is rarely installed on an unmanned aerial vehicle, so that the unmanned aerial vehicle is easy to damage due to collision with the ground when landing, and improvement needs to be made.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a radome fairing buffering formula unmanned aerial vehicle to solve above-mentioned technical problem.

The utility model discloses a solve above-mentioned technical problem, adopt following technical scheme to realize:

the utility model provides a radome fairing buffering formula unmanned aerial vehicle, includes the unmanned aerial vehicle body, unmanned aerial vehicle body bottom surface is provided with a plurality of mounting panels, the mounting panel is connected with unmanned aerial vehicle body bottom surface through a plurality of installation screw rods, the mounting panel bottom surface has set firmly the buffering intubate perpendicularly, it has the buffering inserted bar to peg graft in the buffering intubate, buffering inserted bar lower extreme and buffer board rigid coupling, the cover is equipped with buffer spring on the buffering inserted bar, buffer spring top and buffering intubate rigid coupling, buffer spring lower extreme and buffer board rigid coupling, the buffer board bottom surface has set firmly the gasbag.

Preferably, the right side of the air bag is provided with an air valve.

Preferably, unmanned aerial vehicle body top surface is provided with the canvas, a plurality of holding tanks have been seted up to unmanned aerial vehicle body inside, the holding tank is located canvas edge below, be provided with in the holding tank and connect the rope, go up and connect rope upper end and canvas edge rigid coupling, go up and connect rope lower extreme and fixed column rigid coupling, the fixed column lower extreme is connected rope upper end rigid coupling down, connect rope lower extreme and fixed block rigid coupling down, fixed block and holding tank bottom surface rigid coupling, unmanned aerial vehicle is originally internal to have set firmly miniature electric telescopic handle, miniature electric telescopic handle's flexible end stretches into in the holding tank and cooperates with the fixed column grafting.

Preferably, the miniature electric telescopic rod is wirelessly connected with the controller.

Preferably, go up to connect the rope and connect the rope down and all be the nylon rope, connect the folding storage in holding tank bottom of rope down.

Preferably, the canvas is circular.

The utility model has the advantages that:

when unmanned aerial vehicle landed, the gasbag can effectively play the cushioning effect, and when unmanned aerial vehicle landed, the buffering inserted bar made buffer spring compressed in inserting the buffering inserted tube, impact force when can effectively mitigateing the landing, prevented that unmanned aerial vehicle from damaging to when unmanned aerial vehicle falls because of the accident out of control, break away from with the fixed column through the flexible end of controlling miniature electric telescopic handle, can make the canvas rise and expand, delay unmanned aerial vehicle's falling speed.

Drawings

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

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

FIG. 3 is an enlarged view of a portion B of FIG. 1 according to the present invention;

reference numerals: 1-an unmanned aerial vehicle body; 2-canvas; 3-a buffer plate; 4-buffer inserted link; 5-buffering intubation; 6-a buffer spring; 7-inflating valve; 8-air bag; 9-installing a screw rod; 10-mounting a plate; 11-connecting a rope; 12-accommodating grooves; 13-fixed column; 14-a telescopic end; 15-lower connecting rope; 16-fixing block; 17-micro electric telescopic rod.

Detailed Description

In order to make the technical means, the creation features, the achievement purposes and the functions of the present invention easy to understand, the present invention will be further explained below with reference to the following embodiments and the accompanying drawings, but the following embodiments are only the preferred embodiments of the present invention, and not all embodiments are included. Based on the embodiments in the implementation, other embodiments obtained by those skilled in the art without any creative work belong to the protection scope of the present invention.

Specific embodiments of the present invention will be described below with reference to the accompanying drawings.

Example 1

As shown in fig. 1-3, a radome fairing buffering formula unmanned aerial vehicle, including unmanned

aerial vehicle body

1, 1 bottom surface of unmanned aerial vehicle body is provided with a plurality of mounting panels 10, mounting panel 10 is connected with 1 bottom surface of unmanned aerial vehicle body through a plurality of installation screw rods 9, mounting panel 10 bottom surface has set firmly buffering intubate 5 perpendicularly, it has buffering inserted bar 4 to peg graft in the buffering intubate 5, 4 lower extremes of buffering inserted bar and buffer board 3 rigid couplings, the cover is equipped with buffer spring 6 on the buffering inserted bar 4, 6 tops of buffer spring and 5 rigid couplings of buffering intubate, 6 lower extremes of buffer spring and 3 rigid couplings of buffer board, 3 bottom surfaces of buffer board have set firmly gasbag 8, 8 right sides of gasbag are provided with inflating valve 7. When unmanned aerial vehicle body 1 lands, gasbag 8 plays the cushioning effect with the ground contact, and cushions 4 insert and cushion 5 interior messenger buffer spring 6 compressed of intubate of inserted bar during the landing, impact force when can effectually alleviating unmanned aerial vehicle body 1 lands, and setting up of gasbag 8 can make unmanned aerial vehicle body 1 descend on the surface of water.

Example 2

As shown in fig. 1 to 3, in the case where the other parts are the same as those of embodiment 1, this embodiment is different from embodiment 1 in that: 1 top surface of unmanned aerial vehicle body is provided with canvas 2, canvas 2 is circular, a plurality of holding tanks 12 have been seted up to 1 inside of unmanned aerial vehicle body, holding tank 12 is located canvas 2 edge below, be provided with in the holding tank 12 and connect rope 11, on connect 11 upper ends of rope and canvas 2 edge rigid coupling, on connect 11 lower extremes of rope and fixed column 13 rigid coupling, fixed column 13 lower extreme and the 15 upper end rigid couplings of lower connection rope, connect 15 lower extremes of rope and the 16 rigid couplings of fixed block down,

fixed block

16 and 12 bottom surface rigid couplings of holding tank, on connect rope 11 and lower connection rope 15 all be the nylon rope, connect 15 folding accomodations of rope in holding tank 12 bottoms down, unmanned aerial vehicle body 1 internal stability has miniature electric telescopic handle 17, the flexible end 14 of miniature electric telescopic handle 17 stretches into in

holding tank

12 and 13 grafting cooperation with fixed column, miniature electric telescopic handle 17 and controller wireless connection. When the unmanned aerial vehicle body 1 falls because of accident out of control, retract through controller control miniature electric telescopic handle 17, make flexible end 14 break away from with fixed column 13 to make on connect rope 11 and connect rope 15 down and throw out in accommodating groove 12, make canvas 2 rise and expand, delay unmanned aerial vehicle's falling speed.

The foregoing shows and describes the general principles, essential features, and advantages of the invention. It should be understood by those skilled in the art that the present invention is not limited by the above embodiments, and the description in the above embodiments and the description is only preferred examples of the present invention, and is not intended to limit the present invention, and that the present invention can have various changes and modifications without departing from the spirit and scope of the present invention, and these changes and modifications all fall into the scope of the claimed invention. The scope of the invention is defined by the appended claims and equivalents thereof.

Claims

1. The utility model provides a radome buffer formula unmanned aerial vehicle, includes unmanned aerial vehicle body (1), its characterized in that:

unmanned aerial vehicle body (1) bottom surface is provided with a plurality of mounting panels (10), mounting panel (10) are connected with unmanned aerial vehicle body (1) bottom surface through a plurality of installation screw rod (9), mounting panel (10) bottom surface has set firmly buffering intubate (5) perpendicularly, it has buffering inserted bar (4) to cushion intubate (5) interpolation joint, buffering inserted bar (4) lower extreme and buffer board (3) rigid coupling, the cover is equipped with buffer spring (6) on buffering inserted bar (4), buffer spring (6) top and buffering intubate (5) rigid coupling, buffer spring (6) lower extreme and buffer board (3) rigid coupling, buffer board (3) bottom surface has set firmly gasbag (8).

2. A fairing-buffered drone as claimed in claim 1, characterised in that: and the right side of the air bag (8) is provided with an air valve (7).

3. A fairing-buffered drone as claimed in claim 1, characterised in that: the top surface of the unmanned aerial vehicle body (1) is provided with canvas (2), a plurality of holding grooves (12) are arranged inside the unmanned aerial vehicle body (1), the holding tank (12) is positioned below the edge of the canvas (2), an upper connecting rope (11) is arranged in the holding tank (12), the upper end of the upper connecting rope (11) is fixedly connected with the edge of the canvas (2), the lower end of the upper connecting rope (11) is fixedly connected with the fixing column (13), the lower end of the fixed column (13) is fixedly connected with the upper end of a lower connecting rope (15), the lower end of the lower connecting rope (15) is fixedly connected with a fixed block (16), the fixing block (16) is fixedly connected with the bottom surface of the accommodating groove (12), a miniature electric telescopic rod (17) is fixedly arranged in the unmanned aerial vehicle body (1), the telescopic end (14) of the miniature electric telescopic rod (17) extends into the accommodating groove (12) to be matched with the fixing column (13) in an inserting mode.

4. A fairing buffered drone as claimed in claim 3, characterised in that: the miniature electric telescopic rod (17) is in wireless connection with the controller.

5. A fairing buffered drone as claimed in claim 3, characterised in that: go up and connect rope (11) and connect rope (15) down and all be the nylon rope, connect rope (15) folding accomodating in holding tank (12) bottom down.

6. A fairing buffered drone as claimed in claim 3, characterised in that: the canvas (2) is circular.