Aircraft brake system with air over-pressure alarming function and control method

Abstract

The invention provides an aircraft brake system with an air over-pressure alarming function and a control method. The aircraft brake system with the air over-pressure alarming function comprises a hydraulic switch; a state signal output port of the hydraulic switch communicates with an input end of a pressure collection interface of an anti-skid braking control box; and a hydraulic pressure collection port communicates with a hydraulic pipeline of a working oil port of a brake device. A working oil port of an electro-hydraulic pressure servo valve is accessed into a hydraulic pipeline. A powersupply input end of a right landing gear ground switch communicates with a cathode of a circuit protection automatic switch; and a power supply output end of the right landing gear ground switch communicates with a power supply input end of a left landing gear ground switch. A power supply output end of the left landing gear ground switch communicates with a signal collection interface of a sliding brake control box ground switch. According to the aircraft brake system with the air over-pressure alarming function, by using the hydraulic switch to detect the pressure of a brake pipeline, the over-pressure situation in an air brake system of an aircraft is found earlier and treated earlier to avoid a fault that the aircraft lands with pressure when the aircraft has no ground protection function or ground protection of the aircraft fails to work; and therefore, tire burst accidents are prevented, and the aircraft landing braking safety and reliability are enhanced.

Description

technical field [0001] The invention relates to the field of aircraft anti-skid braking systems, in particular to an aircraft braking system with an air residual pressure alarm function and a control method thereof. Background technique [0002] The prior art aircraft digital fly-by-wire anti-skid brake system is composed of a brake command sensor 1, an anti-skid brake control box 2, a wheel speed sensor 3, an electro-hydraulic pressure servo valve 4 and an electromagnetic hydraulic lock 5, and has an anti-skid brake function. Brake command sensor 1, anti-skid brake control box 2, electro-hydraulic pressure servo valve 4, electromagnetic hydraulic lock 5 to realize the braking function; anti-skid brake control box 2, wheel speed sensor 3, electro-hydraulic pressure servo valve 4 and electromagnetic hydraulic lock 5 to realize Anti-slip function. [0003] The structural block diagram of the normal brake system of the prior art aircraft digital fly-by-wire anti-skid brake sys...

AI Technical Summary

Problems solved by technology

[0014] In order to solve the problem that the aircraft braking system in the prior art lands under pressure and cause the tire of the aircraft braking system to blow out, the present invention proposes an aircraft braking system and a control method with an air residual pressure alarm function

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