Architecture of landing gear control system of aircraft

Abstract

The invention relates to a landing gear control system, in particular to an architecture of a landing gear control system of an aircraft with high safety. The landing gear control system comprises a landing gear retraction and extension system (1), a wheel brake system (2) and a front wheel steering system (3), wherein controllers in the system are subject to data exchange via a bus; landing gear retraction and extension controllers (11) and (12) are used for providing empty land signals for the front wheel steering system (3) and the wheel brake system (2), so as to convert the empty land control states of the system; when the front wheel steering system (3) fails, a shimmy damping mode is started; the ground direction of an aircraft is controlled by the wheel brake system (2) through a differential brake. The architecture of the landing gear control system of the aircraft has the advantage of high safety.

Description

technical field [0001] The invention relates to a landing gear control system, in particular to an aircraft landing gear control system architecture with high safety. Background technique [0002] In the traditional aircraft landing gear control system architecture design, the landing gear retraction system is generally equipped with normal retraction and emergency release, and the normal control is mechanical or electrical single redundancy, the failure rate is high, and the emergency release of the landing gear mostly uses air-conditioning. Emergency release, once the emergency release cannot be performed, the pilot cannot normally retract and retract the landing gear. The wheel braking system basically adopts the mode of normal braking and emergency braking, and the normal braking is electrical single redundancy. Once a failure occurs, it will be directly transferred to the emergency braking, which is less safe. The emergency braking mostly uses high-pressure air-conditio...

AI Technical Summary

Problems solved by technology

[0002] In the traditional aircraft landing gear control system architecture design, the landing gear retraction system is generally equipped with normal retraction and emergency release, and the normal control is mechanical or electrical single redundancy, the failure rate is high, and the emergency release of the landing gear mostly uses air-conditioning. Emergency release, once the emergency release is not possible, the pilot cannot normally retract the landing gear

The wheel braking system basically adopts the mode of normal braking and emergency braking, and the normal braking is electrical single redundancy. Once a failure occurs, it will be directly transferred to the emergency braking, which is less safe. The emergency braking mostly uses high-pressure air-conditioning, and the braking is Difficult to control and difficult to restore the system

The turning system mostly adopts mechanical or electrical control. Once the turning control fails, the turning function needs to be manually disconnected, which increases the burden on the pilot.

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