Control system and method for helicopter electrically-driven tail rotor

Abstract

The invention relates to a control system and method for a helicopter electrically-driven tail rotor. The control system comprises a pedal, an angular displacement sensor, a helicopter controller, a motor controller, a driver for a tail rotor driving motor, a motor driver of a tail rotor variable pitch structure, a detection unit, a gyroscope, a motor-reducer integrated structure capable of driving the tail rotor to rotate, and an electrically-driven variable pitch structure. By use of the control method, according to a pedal angle change and a helicopter tail gesture change of gyroscope detection, the revolving speed of the tail rotor driving motor is automatically controlled, and a variable pitch structure is regulated so as to realize the balance or the diversion of the helicopter. Theinvention provides the control system and method for the helicopter electrically-driven tail rotor, and replaces the internal combustion engine driving and the excessive transmission shaft of a traditional helicopter, so that the quick and stable automatic balance and diversion of the helicopter can be realized, operation difficulty is reduced, and reliability and stability are enhanced so as to be favorable for accelerating the technology of an electric helicopter to be progressed and developed.

Description

technical field [0001] The invention relates to the field of helicopter design and control, in particular to a helicopter electric drive tail rotor control system and method. Background technique [0002] The power source of the traditional helicopter tail rotor is generally from the main engine, which is transmitted to the tail rotor through the reducer and the transmission shaft. At present, the helicopter tail rotor is generally composed of intermediate reducer, tail drive shaft, tail reducer, tail rotor pitch change rod and other components, wherein the intermediate reducer, tail drive shaft, and tail reducer transfer the energy from the main reducer to Tail rotor, which drives the tail rotor to rotate; the pilot controls the pedal to drive the tail rotor pitch change rod through the control line, thereby changing the angle of attack of the tail rotor blade and changing the thrust (pull force) of the tail rotor blade to achieve the purpose of helicopter balance or direct...

AI Technical Summary

Problems solved by technology

[0003] The existing helicopter tail rotor system has the characteristics of large structural weight, large energy loss, large vibration and noise, possible jamming of the control rod system, difficulty in assembly and maintenance, etc.

The existing variable pitch structure of helicopters mostly uses a worm gear mechanism to control the movement of the variable pitch ring, and the structure is relatively complicated.

Moreover, in the variable-pitch operation, the helicopter balance and steering are controlled entirely by the driver stepping on the pedals. The driving is difficult and unstable, and it is easy to vibrate.

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