CN110877726A

CN110877726A - Foldable unmanned aerial vehicle

Info

Publication number: CN110877726A
Application number: CN201911101890.4A
Authority: CN
Inventors: 苏嵩; 梅玉洁
Original assignee: Xuzhou Divo Communication Engineering Co Ltd
Current assignee: Xuzhou Divo Communication Engineering Co Ltd
Priority date: 2019-11-12
Filing date: 2019-11-12
Publication date: 2020-03-13

Abstract

The invention discloses a foldable and deformable quadrotor which runs in a quadrotor mode under the condition of carrying cargo and has the characteristics of large carrying capacity, good stability and the like. In order to facilitate the rapid shuttling of the aircraft in a complex outdoor environment under the condition of no load, the scheme improves the motion flexibility of the aircraft through four folding rotors, and improves the stability of the dual-rotor aircraft through an electromagnetic directional valve.

Description

Foldable unmanned aerial vehicle

Technical Field

The invention relates to a folding unmanned aerial vehicle.

Background

The unmanned aerial vehicle at present can not realize the flight purpose of different volumes of free rotatory folding realization.

Disclosure of Invention

1. Technical problem to be solved

The invention aims to provide a foldable and deformable quadrotor which is designed to operate in a quadrotor mode under the condition of carrying cargo and has the characteristics of large carrying capacity, good stability and the like. In order to facilitate the rapid shuttling of the aircraft in a complex outdoor environment under the condition of no load, the scheme improves the motion flexibility of the aircraft through four folding rotors, and improves the stability of the dual-rotor aircraft through an electromagnetic directional valve.

2. Technical scheme

In order to solve the above problems, the present invention adopts the following technical solutions.

A foldable unmanned aerial vehicle, which comprises a vehicle body,

comprises two skeletons with the same structure,

the framework is composed of a first connecting rod, a second connecting rod, a third connecting rod and a fourth connecting rod,

a rotor wing assembly is arranged at the joint of the first connecting rod and the second connecting rod, the first connecting rod and the fourth connecting rod are fixedly connected to form a vertical angle,

a rotor wing component is arranged at the joint of the third connecting rod and the fourth connecting rod,

the two frameworks are symmetrically arranged, and the two frameworks are symmetrically arranged,

the two skeletons are connected through a folding rotary steering engine, namely the folding rotary steering engine is arranged at the joint of the first connecting rod and the fourth connecting rod, so that the two skeletons are folded and symmetrical through the driving of the folding rotary steering engine,

wherein, an electromagnet is arranged at the joint of the second connecting rod and the third connecting rod of one framework, a permanent magnet is arranged at the joint of the second connecting rod and the third connecting rod of the other framework, after being folded, the two frameworks are fastened and jointed through the electromagnet,

the rotor wing assembly comprises a frame, a supporting beam, a rotating motor and a propeller, the supporting beam is fixed on the frame, the rotating motor is fixed on the supporting beam, the propeller is arranged on the rotating motor,

the frame all be equipped with two sets of electromagnetic directional valves, two sets of electromagnetic directional valves symmetry installation, after folding, the electromagnetic directional valve of the rotor subassembly of laminating from top to bottom all is on same vertical line, the air current of electromagnetic directional valve control gas outlet, and then realize the steady operation of two rotors.

The frame is also provided with supporting feet.

Advantageous effects

Compared with the prior art, the invention has the advantages that:

through controlling the two rotors on the single side and the folding rotary steering engine, the folding of the rack can be successfully realized, after the folding, the fastening of the connecting frame is realized through the electromagnet, and the rack is tightly attached. At the moment, the double-rotor aircraft is actually two groups of rotor aircraft, a single group of rotors consists of two rotors, the rotating directions of an upper rotating motor and a lower rotating motor are opposite, the rotating speed of the upper motor is greater than that of the lower motor, air flow with high pressure is formed between the two rotors, the air flow at an air outlet is controlled by controlling an electromagnetic directional valve arranged on a rack, and then the stable operation of the double rotors is realized.

The technical advantages are as follows:

1. has strong loading capacity when unfolded

2. Has stronger motion performance after being folded.

Drawings

FIG. 1 is a schematic axial view of the present invention,

FIG. 2 is a schematic top view of the present invention,

figure 3 is a schematic view of the load operation of the present invention,

figure 4 is a front view of the present invention in load operation,

figure 5 is a schematic axial view of the folded state of the present invention,

figure 6 is a front view schematically showing the folded state of the present invention,

fig. 7 is a schematic top view of the folded state of the present invention.

Detailed Description

The drawings in the embodiments of the invention will be combined; the technical scheme in the embodiment of the invention is clearly and completely described; obviously; the described embodiments are only some of the embodiments of the invention; but not all embodiments, are based on the embodiments of the invention; all other embodiments obtained by a person skilled in the art without making any inventive step; all fall within the scope of protection of the present invention.

In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "top/bottom", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplification of description, 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. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "disposed," "sleeved/connected," "connected," and the like are to be construed broadly, e.g., "connected," which may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

Example 1:

comprises two skeletons 5 with the same structure,

a rotor wing assembly is arranged at the joint of the first connecting rod 5.1 and the second connecting rod 5.2, the first connecting rod and the fourth connecting rod are fixedly connected to form a vertical angle,

a rotor component is arranged at the joint of the third connecting rod 5.3 and the fourth connecting rod 5.4,

the two skeletons are connected through a folding rotary steering engine 9, namely the folding rotary steering engine 9 is arranged at the joint of the first connecting rod and the fourth connecting rod, so that the two skeletons are symmetrically folded through the driving of the folding rotary steering engine,

wherein, an electromagnet 7 is arranged at the joint of the second connecting rod and the third connecting rod of one framework, a permanent magnet 6 is arranged at the joint of the second connecting rod and the third connecting rod of the other framework, after being folded, the two frameworks are fastened and jointed through the electromagnet,

the rotor wing assembly comprises a frame 1, a supporting beam 2, a rotating motor 3 and a propeller 4, wherein the supporting beam 2 is fixed on the frame 1, the rotating motor 3 is fixed on the supporting beam 2, the propeller 4 is arranged on the rotating motor 3,

the frame all be equipped with two sets of electromagnetic directional valves 13, two sets of electromagnetic directional valves symmetry installation, after folding, the electromagnetic directional valve of the rotor subassembly of laminating from top to bottom all is on same vertical line, the air current of electromagnetic directional valve control gas outlet 12, and then realize the steady operation of two rotors.

The frame is also provided with support feet 8,

Claims

1. A foldable unmanned aerial vehicle, its characterized in that:

comprises two skeletons with the same structure,

the two frameworks are symmetrically arranged.

2. A folding drone according to claim 1, characterised in that: the two frameworks are connected through a folding rotary steering engine, namely the folding rotary steering engine is arranged at the connecting part of the first connecting rod and the fourth connecting rod, so that the two frameworks are folded and symmetrical under the driving of the folding rotary steering engine;