Double-set rigid control system for aircraft

Abstract

The invention provides a double-set rigid control system for an aircraft. The double-set rigid control system for the aircraft comprises a double-set rigid elevator control system and a double-set rigid aileron control system, wherein the double-set rigid elevator control system comprises a left side elevator control line system, a right side elevator control line system and an elevator releasing mechanism; and the double-set rigid aileron control system comprises a left side aileron control line system, a right side aileron control line system and a aileron releasing mechanism. When one side control line system is blocked or a single side control surface is jammed, a driver can exert the left side control line systems and the right side control line systems to recover independent states by using the releasing mechanisms and control the corresponding side control surfaces to deflect by using failure-free side control line systems so as to ensure that the aircraft can return and land safely.

Description

technical field [0001] The invention relates to the field of aircraft control systems, in particular to a double-set hard elevator control system and a double-set hard aileron control system. Background technique [0002] The main control system of the aircraft includes the aileron control system, the elevator control system and the rudder control system. At present, the three main control systems of some old models all adopt the configuration of a single set of hard mechanical control system composed of rocker rods. Taking the elevator control system of MA60 aircraft as an example, it consists of the steering column in the cockpit and the The left side of the aircraft is composed of rocker rods that run through the cockpit to the tail of the aircraft in sequence. When the steering column is manipulated during delay, the control force cannot be transmitted from the stuck and interrupted control line to the elevator rudder surface. Therefore, the pilot will not be able to co...

AI Technical Summary

Problems solved by technology

At present, the three main control systems of some old models all adopt the configuration of a single set of hard mechanical control system composed of rocker rods. Taking the elevator control system of MA60 aircraft as an example, it consists of the steering column in the cockpit and the The left side of the aircraft is composed of rocker rods that run through the cockpit to the tail of the aircraft in sequence. When the steering column is manipulated during delay, the control force cannot be transmitted from the stuck and interrupted control line to the elevator rudder surface. Therefore, the pilot will not be able to control the pitch attitude of the aircraft by controlling the elevator rudder surface; or when the elevator unilaterally When the rudder surface is jammed, the pilot cannot use the limited manpower to push the steering column to drive the rudder surface on the non-faulty side to deflect, which will also cause the pilot to be unable to control the pitch attitude of the aircraft by controlling the elevator rudder surface, and eventually the aircraft may not be safe. Return and landing

[0003] To sum up, there is a possibility of single-point mechanical failure in the configuration of this single set of hard mechanical control system, that is, when the control line is stuck or the rudder surface is stuck on one side, there is no effective means to ensure the driver's control over the control system. The control ability of the main rudder surface of the aircraft may lead to the uncontrollable attitude of the aircraft, which will eventually lead to the inability of the aircraft to return and land safely

Images