Multi-rotor unmanned aerial vehicle capable of being quickly folded

A multi-rotor unmanned aerial vehicle, fast technology, applied in the direction of rotorcraft, unmanned aircraft, fuselage, etc., can solve the problem that the arm is not easy to be transported and stored as a whole, so that the structural performance is not affected and normal use is guaranteed , the effect of reducing the occupied space

Pending Publication Date: 2022-03-22
FUDAN UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] Aiming at the problem that the arm of the multi-rotor UAV in the prior art is not easy to be transporte

Method used

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  • Multi-rotor unmanned aerial vehicle capable of being quickly folded
  • Multi-rotor unmanned aerial vehicle capable of being quickly folded
  • Multi-rotor unmanned aerial vehicle capable of being quickly folded

Examples

Experimental program
Comparison scheme
Effect test

Example Embodiment

[0028] Example 1

[0029] A fast foldable multi-rotor drone, such as Figure 1-3 As shown, it includes a fuselage 1 , a plurality of arms 2 mounted on the fuselage 1 , and a power assembly 3 mounted on each of the arms 2 . Among them, the fuselage 1 is configured as a rectangular shell as a whole, and components such as a power supply, flight control equipment, and communication equipment for supporting flight are mounted in the fuselage 1 . Among them, the arms 2 are preferably arranged in a cylindrical structure, and there are four arms 2 , and the four arms 2 are symmetrically mounted on two opposite sides of the fuselage 1 in pairs and located in the fuselage 1 . The two arms 2 on the same side are located at two ends of the fuselage 1 respectively, that is, the multi-rotor UAV has an H-shaped structure when in use. In other preferred embodiments, the installation position of the arms 2 may also be suitable for a multi-rotor unmanned aerial vehicle in an X shape or a + s...

Example Embodiment

[0034] Embodiment 2

[0035] The difference from the first embodiment is that this embodiment proposes another structural form of the fixing mechanism 4. In this embodiment, as Figure 4As shown, the fixing mechanism 4 is configured as a limit bracket 44 that is fixedly installed on the fuselage 1. The limit bracket 44 is provided with a limit groove that is adapted to the outer side wall of the machine arm 2, and the limit groove is made of elastic material. , and the opening of the limit slot is smaller than the diameter of the machine arm 2 . In this embodiment, the limiting bracket 44 is configured in a cylindrical shape as a whole, and an axially extending through groove is formed on the circumferential side wall of the limiting bracket 44, so that the cylindrical limiting bracket having the through groove is formed. 44 constitutes the above-mentioned limiting groove. With this arrangement, when the arm 2 rotates to the limit slot on the limit bracket 44, the limit slot...

Example Embodiment

[0036] Embodiment 3

[0037] The difference from the first embodiment is that: in this embodiment, the above-mentioned fixing mechanism 4 includes two lock sleeves 42, the two lock sleeves 42 are fixedly connected to each other, and the axial gaps 43 on the two lock sleeves 42 communicate with each other. , so that the machine arm 2 can rotate from one of the lock sleeves 42 to the other lock sleeve 42 during the rotation process, such as Figure 5 shown. The two locking sleeves 42 are respectively used to fix the arm 2 in the above-mentioned flying position and the folded position. In addition, the two lock sleeves 42 can be arranged to be perpendicular to each other. And it can be understood that the hinge point (that is, the hinge 12) between the arm 2 and the fuselage 1 is located at the position where the axes of the two lock sleeves 42 intersect, so as to ensure that the arm 2 can be in the folded position and the flying position. The lock sleeves 42 are coaxial, so a...

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Abstract

The invention discloses a multi-rotor unmanned aerial vehicle capable of being quickly folded, and belongs to the field of unmanned aerial vehicles, the multi-rotor unmanned aerial vehicle comprises a vehicle body, a plurality of vehicle arms mounted on the vehicle body and power assemblies mounted on the vehicle arms, and each vehicle arm is connected with the vehicle body through a hinge so that the vehicle arms can rotate between a flight position and a folding position relative to the vehicle body; the fuselage is at least provided with fixing mechanisms corresponding to all the vehicle arms, and the fixing mechanisms are used for fixing the vehicle arms located at the flying position. The multi-rotor unmanned aerial vehicle is simple in structure and reasonable in design, and the size of the multi-rotor unmanned aerial vehicle during transportation and storage can be reduced by folding the vehicle arms while the flight performance of the multi-rotor unmanned aerial vehicle is not affected.

Description

technical field [0001] The invention relates to the field of unmanned aerial vehicles, in particular to a rapidly foldable multi-rotor unmanned aerial vehicle. Background technique [0002] With the rapid development of UAV-related technologies at home and abroad, there are many types of UAV systems and distinctive features, resulting in great differences in size, quality, range, flight time, flight altitude, flight speed, and tasks. Due to the diversity of UAVs, there will be different classification methods for different considerations: according to the configuration of the flight platform, UAVs can be divided into fixed-wing UAVs, rotary-wing UAVs, unmanned airships, parachute Drones, flapping wing drones, etc. [0003] Among them, the multi-rotor UAV is a special unmanned helicopter with three or more rotor shafts. According to the classification of aircraft structure, multi-rotor UAVs are mainly divided into "X", "+" and "H" UAVs. Multi-rotor UAVs have smaller fuselag...

Claims

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Application Information

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IPC IPC(8): B64C1/30B64C27/08
CPCB64C1/30B64C27/08B64U10/10
Inventor 龚帮民艾剑良
Owner FUDAN UNIV
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