Pitch-variable tricopter

A technology of variable pitch and aircraft, applied in aircraft, rotorcraft, motor vehicles, etc., can solve the problems of poor anti-interference ability, large coupling, limited load, etc., and achieve the effect of flight stability and strong anti-interference ability.

Inactive Publication Date: 2011-12-21
ZHONGBEI UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] In order to overcome the shortcomings of existing multi-axis aircraft such as poor anti-interference ability, large coupling, complex and expensive auxiliary electronic equipment, incompatibility with helicopter flight control systems on the market, limited load, and underutilization of motor power, etc.

Method used

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Embodiment Construction

[0019] The embodiment will be further described in conjunction with the accompanying drawings. This embodiment is used to illustrate the present invention, but not to limit the present invention.

[0020] The specific embodiment is that the motor (20) transmits the power to the propeller through the motor tooth (18), the large tooth (17), the gear seat (23) main shaft (12), the middle joint (5), and the paddle clamp (1), which generates Lift force; by the steering gear (14) through the rudder plate (13), connecting rod (11), double-headed rocker arm (9), single-headed rocker arm (10), connecting rod (15), push plate jacket (16), The push plate (6), the connecting rod (4), and the paddle clip (1) control the rapid and precise change of the lift of the rotor. The angle change of the guide vane (24) installed on the tailpipe (26) is controlled by the steering gear, and the moment to the center of gravity is generated under the action of the downward swirl of the rotor to offset t...

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Abstract

The purpose of the present invention is to provide a kind of variable-pitch three-rotor aircraft. The variable-pitch three-rotor aircraft adopts a three-axis structure. Each axis adopts a rotor with a large diameter and low speed. The speed is set at a constant value. The pitch difference controls the balance of the pitching direction of the aircraft. A guide vane with a variable angle is designed under one of the rotors. Under the action of the down swirl generated by the rotor, by changing the angle between the guide vane and the down swirl, the The force of the downward swirl on the deflector, the moment of the force on the center of gravity cancels the counter moment of the rotor. The invention comprises a variable-pitch rotor, a guide vane, a tail pipe and a fuselage. The aircraft has stable flight and strong anti-interference ability, and is especially suitable as an aerial platform for small unmanned aircraft and aerial photography aircraft.

Description

technical field [0001] The invention relates to a novel aircraft, in particular to a pitch-variable three-rotor aircraft. Background technique [0002] At present, multi-rotor aircraft are mainly divided into two categories, even-numbered axes and odd-numbered axes. The even-numbered axis multi-rotor aircraft is characterized by several axes distributed around the fuselage, each axis is directly driven by a motor with a fixed pitch propeller, half of the motors rotate clockwise, and the other half rotates counterclockwise, and the pitch of the aircraft is controlled by coordinating the speed of each motor Balance and anti-moment balance; the structure of odd-numbered-axis multi-rotor aircraft is consistent with that of even-numbered-axis multi-rotors. To offset the excess reaction torque. However, the current multi-rotor aircraft has the following disadvantages, [0003] 1. The control system is extremely complex. The flight control problem is a key problem of small mult...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/08B64C27/32
Inventor 杨润李晓杰
Owner ZHONGBEI UNIV
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