CN101704412A

CN101704412A - Six-rotor aircraft

Info

Publication number: CN101704412A
Application number: CN200910217901A
Authority: CN
Inventors: 白越; 孙强; 李也凡; 高庆嘉
Original assignee: Changchun Institute of Optics Fine Mechanics and Physics of CAS
Current assignee: Changchun Institute of Optics Fine Mechanics and Physics of CAS
Priority date: 2009-11-24
Filing date: 2009-11-24
Publication date: 2010-05-12

Abstract

The invention relates to an unmanned aircraft, in particular to a six-rotor aircraft, comprising an engine body, six support arms connected on the periphery of the engine body, six rotors respectively arranged on the end part of each support arm, and an electronic control system which is arranged in the engine body and is connected with each rotor in a controlled manner. The geometric center lines of the six support arms are in the same plane, and the included angle of the geometric center lines of each two adjacent support arms is 60 degrees. The aircraft has high maneuverability, can realize change in any direction in flight such as vertical landing, rapid forward flight, upside down flight, hovering and fight the like. Therefore, the aircraft has maneuvering property superior to that of any one aircraft used currently.

Description

Six-rotor aircraft

Technical field

The present invention relates to unmanned vehicle, particularly a kind of many rotor aerial vehicles of new structure.

Background technology

Current most of aircraft all is a fixed-wing formula aircraft, and this aircraft can't be finished vertical and landing takeoff, needs special-purpose runway or feedway, and its maneuvering performance is limited.Lifting vehicle has the vertical and landing takeoff function, can also aloft hover, have demand widely in fields such as military surveillance, anti-terrorism, public security, fire-fighting, forest inspection, nuclear leakage detection and the disaster relief, but the manoevreability of current lifting vehicle and stability are also not enough.Particularly the military conflict major part of our times all is the small-scale military conflict in subrange, the fight occasion mostly occurs under the urban background, especially the war against terror that grows in intensity, under the urban background enemy's scouting, supervision and position are determined etc. to require more and more important, require applied aircraft to have the manoevreability of superelevation.Current lifting vehicle mainly contains single rotor (main rotor+tail-rotor) helicopter, the two outstanding wing (contrarotation) helicopter and three kinds of versions of four rotor crafts, such as four rotor crafts of the MH-16 helicopter of U.S. McDonnell-Douglas Corporation, Muscovite card-29 helicopter, German Microdrone company etc.Above-mentioned rotor craft self all is a motion coupled system, and in-flight direction and attitude are coupled, alerting ability and less stable, and the lift of aircraft and weight ratio are lower, and load capacity is very poor when being designed to small aircraft.

Summary of the invention

The objective of the invention is existingly have vertical takeoff and landing and the motion of aircraft of the function of hovering and attitude changes coupling, alerting ability and poor stability, lift and weight ratio are lower and problem such as miniaturization performance deficiency, proposes a kind of six-rotor aircraft with new structure of attitude stability highly and controllability for solving.

Six-rotor aircraft of the present invention, comprise body, the six roots of sensation hold-down arm on being connected around the body, be separately positioned on six rotors on each hold-down arm end and be arranged on the electric-control system of each rotor of control linkage in the body that the geometric center lines of described six roots of sensation hold-down arm at grade, the geometric center lines angle of each two adjacent hold-down arm is 60 degree.

Described rotor is motor or the oily mechanism one-tenth that is connected rotor by rotor with direct drive.The plane of rotation of each rotor rotor equates with the interplanar angle in geometric center lines place of described six roots of sensation hold-down arm, and the plane of rotation coplane of two rotor rotors on the same diagonal line, adjacent two rotor rotors hand of rotation opposite.

Each rotor has been eliminated the loss in efficiency of driving system by motor or oily machine direct drive, has improved the lift force of energy utilization efficiency and aircraft.The hand of rotation of adjacent two rotors is opposite, and positive and negative rotor rotated is opposite to the torsional moment of body, therefore can regulate the rotating speed of six rotors and realize that the torsional moment of closing to body is zero.The lift that the interplanar angle of the plane of rotation of rotor rotor and body makes six rotors to body make a concerted effort and resultant moment is distinguished controlled at three axial six components, therefore can make under this aircraft prerequisite that aloft attitude remains unchanged and change sense of motion, also can keep carrying out the attitude adjusting under the sense of motion unmodified prerequisite, can also when changing sense of motion, carry out the change of attitude, realize the full decoupled of motion and attitude.This aircraft has the attitude stability and the controllability of height, has tempting prospect in the military affairs of scouting and be retrieved as main objective with information and anti-terrorism application.

Provided by the invention around the body aircraft of rectangular distribution and non-coplanar six rotors. six rotors are by motor or oily machine direct drive, having improved lift force. the rotating speed control by non-coplanar six rotors has realized the full decoupled of three-axis moving and attitude, this aircraft has the manoevreability of height, can realize vertical takeoff and landing, fly before fast, inverted flight, hover, any direction changes in-flight. therefore, this aircraft provided by the present invention has the maneuvering performance of any aircraft that surpasses current use.

Description of drawings

Fig. 1 is the structural representation of six-rotor aircraft of the present invention;

Fig. 2 is the scheme drawing of rotor structure shown in Fig. 1.

The specific embodiment

The embodiment that provides below in conjunction with accompanying drawing is described in further detail the present invention.

With reference to Fig. 1, a kind of six-rotor aircraft, comprise body 1, the six roots of sensation hold-down arm 2 on being connected around the body 1, be separately positioned on six rotors 3 on each hold-down arm 2 end and be arranged on the electric-control system 4 of each rotor of control linkage in the body 1 that the geometric center lines of described six roots of sensation hold-down arm 2 at grade, the geometric center lines angle of each two adjacent hold-down arm 2 is 60 degree.

With reference to Fig. 2, described rotor 3 is to be made of rotor 3.1 is connected rotor 3.1 with direct drive motor or oily machine 3.2.

The plane of rotation of described each rotor rotor 3.1 equates with the interplanar angle in geometric center lines place of described six roots of sensation hold-down arm 2, and the plane of rotation coplane of two rotor rotors on the same diagonal line, adjacent two rotor rotors hand of rotation opposite.

Claims

1. six-rotor aircraft, it is characterized in that comprising body (1), be connected six roots of sensation hold-down arm (2) that body (1) goes up on every side, be separately positioned on six rotors (3) on each hold-down arm (2) end and be arranged on the electric-control system (4) of each rotor of control linkage in the body (1), the geometric center lines of described six roots of sensation hold-down arm (2) at grade, the geometric center lines angle of each adjacent two hold-down arm (2) is 60 degree.

2. six-rotor aircraft according to claim 1 is characterized in that described rotor (3) is motor or oily machine (3.2) formation that is connected rotor (3.1) by rotor (3.1) with direct drive.

3. six-rotor aircraft according to claim 2, it is characterized in that: the plane of rotation of described each rotor rotor (3.1) equates with the interplanar angle in geometric center lines place of described six roots of sensation hold-down arm (2), and the plane of rotation coplane of two rotor rotors on the same diagonal line, adjacent two rotor rotors hand of rotation opposite.