Multi-axle aircraft

A multi-rotor aircraft and wing-shaft technology, applied in the field of aircraft, can solve the problems of low safety and stability, low efficiency, and the aircraft cannot vertically lift and hover.

Active Publication Date: 2016-02-03
CHINA AIRCRAFT MAINTENANCE & ENG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] Traditional multicopters consume a lot of energy when cruising, have poor stability and safety, and are basically unable to save themselves when they lose part or all of their power
Traditional aircraft cannot lift vertically and hover
Traditional helicopters have high energy consumption, low efficiency, and low safety and stability

Method used

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Examples

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Embodiment Construction

[0009] Now in conjunction with accompanying drawing the present invention is described in detail: a kind of multi-axis aircraft, comprises fuselage 1, left composite wing 2, right composite wing 3, support 4, front rotor 5, rear rotor 6 and landing gear 7. The fuselage 1 is equipped with a control system and airborne equipment. The left compound wing 2 and the right compound wing 3 have the same structure, and they are symmetrically installed on the left and right sides of the fuselage 1. The front rotor 5 and the rear rotor 6 have the same structure, and they are respectively installed at the front and rear ends of the fuselage 1 through brackets. The front rotor 5 and the rear rotor 6 are driven independently by motors respectively. The front rotor 5 and the rear rotor 6 turn in opposite directions, and the rotation speed is convenient to adjust. The front rotor 5 and the rear rotor 6 mainly play the role of pitching and lifting flight attitude control. Landing gear 7 ado...

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PUM

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Abstract

The invention relates to a multi-axle aircraft, which belongs to the technical field of aircrafts. The multi-axle aircraft comprises an aircraft body, a left composite wing, a right composite wing, brackets, a front rotor and a rear rotor and a landing gear. An operating system and airborne equipment are mounted in the aircraft body. The left composite wing and the right composite wing have same structures and are symmetrically mounted on the left and right sides of the aircraft body. The front rotor and the rear rotor have same structures and are respectively mounted at the front and rear ends of the aircraft body through the brackets. The landing gear adopts a wheel type structure or a skid and wheel combined structure. The left composite wing and the right composite wing have same structures and symmetrically mounted on the left and right sides of the aircraft body. Two rows of rotors are mounted in the left composite wing and the right composite wing; and all rotors are driven by a motor. A wing of the left composite wing comprises a front wing and a rear wing, which both can deflect around a wing shaft. The multi-axle aircraft provided by the invention does not need a big landing site and can vertically take off and land. The multi-axle aircraft provided by the invention has the advantages of great lift force, safety, stability and flexibility.

Description

technical field [0001] A multicopter aircraft belongs to the technical field of aircraft, and in particular relates to a multicopter aircraft. Background technique [0002] Traditional multicopters consume a lot of energy when cruising, have poor stability and safety, and are basically unable to save themselves when they lose part or all of their power. Conventional aircraft cannot vertically lift and hover. Traditional helicopters have high energy consumption, low efficiency, and low safety and stability. Contents of the invention [0003] The purpose of the present invention is to overcome the above-mentioned deficiency of traditional multicopter, airplane and helicopter, invent a kind of highly efficient and safe multicopter capable of vertical take-off and landing. [0004] A multi-axis aircraft comprises a fuselage, a left composite wing, a right composite wing, a bracket, a front rotor, a rear rotor and a landing gear. The fuselage is equipped with a control syste...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/22B64C29/00B64C9/00B64C21/00
Inventor 王志成
Owner CHINA AIRCRAFT MAINTENANCE & ENG
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