Architecture of landing gear control system of aircraft

A technology for aircraft landing gear and control systems, applied to aircraft brake arrangements, brake regulators, chassis, etc., can solve problems such as difficult control, low safety, and increased pilot burden, and achieve high safety and security high effect

Inactive Publication Date: 2017-05-17
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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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 no

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  • Architecture of landing gear control system of aircraft

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Embodiment Construction

[0012] The present invention will be further described in detail below in conjunction with the accompanying drawings.

[0013] Such as figure 1 As shown, it is composed of landing gear retractable system 1, wheel brake system 2 and nose wheel steering system 3, hydraulic energy is provided by No. 1 hydraulic system 31 and No. 2 hydraulic system 30, left emergency bus bar 9 and right emergency bus bar 10 provides power, each controller in the system exchanges data through the bus, landing gear retractable controllers 11 and 12 provide open-ground signals to the front wheel steering system 3 and wheel braking system 2, and are used for the conversion of the open-ground control state of the system. When the wheel turning system 3 fails, it enters the swing reduction mode, and the wheel braking system 2 realizes the ground direction control of the aircraft through differential braking. The landing gear retraction system consists of the normal retraction system of the landing gear...

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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...

Claims

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Application Information

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IPC IPC(8): B64C25/26B64C25/30B64C25/48B64C25/46
CPCB64C25/26B64C25/30B64C25/46B64C25/48
Inventor 李振水李胜军常凯贾爱绒罗林
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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