Aircraft braking system capable of preventing mistake output and control method of aircraft braking system

A braking system and anti-skid braking technology, applied in the field of aircraft braking system and its control, can solve problems such as tire blowout of aircraft braking system

Pending Publication Date: 2019-09-06
XIAN AVIATION BRAKE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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 capable of preventing incorrect output and its control method

Method used

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  • Aircraft braking system capable of preventing mistake output and control method of aircraft braking system
  • Aircraft braking system capable of preventing mistake output and control method of aircraft braking system
  • Aircraft braking system capable of preventing mistake output and control method of aircraft braking system

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Embodiment Construction

[0060] This embodiment is based on the braking system of the prior art, and a hydraulic switch is added on the basis of the approaching brake wheel braking device to form an aircraft braking system capable of preventing erroneous output.

[0061] This embodiment includes a brake command sensor 1, an anti-skid brake control box 2, a wheel speed sensor 3, an electro-hydraulic pressure servo valve 4, an electromagnetic hydraulic lock 5, a landing switch, an automatic circuit protection switch 12, a +28V power supply 13, and a hydraulic pressure source 8 And fuel tank 9, wherein said landing switch is divided into left landing gear landing switch 10 and right landing gear landing switch 11.

[0062] The positive pole of the +28VDC power supply 13 is connected with the positive pole of the automatic circuit protection switch 12, the negative pole of the automatic circuit protection switch 12 is connected with the power input terminal of the right landing gear landing switch 11, and ...

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PUM

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Abstract

The invention discloses an aircraft braking system capable of preventing mistake output and control method of the aircraft braking system. The aircraft braking system comprises a hydraulic switch, anoutput port of a state signal of the hydraulic switch communicates with the input end of the pressure acquisition interface of an anti-skid brake control box, and the hydraulic pressure acquisition port of the hydraulic switch communicates with a working oil port of a brake device; and a working oil port of an electro-hydraulic pressure servo valve is connected with a hydraulic pipeline. The powerinput end of a right landing gear landing switch communicates with the negative pole of a circuit protection automatic switch, and the output end of the right landing gear landing switch communicateswith the power input end of a left landing gear landing switch; and the power output end of the left landing gear landing switch communicates with the landing switch signal acquisition interface of the anti-skid brake control box. According to the aircraft braking system, the air / ground state of the aircraft is determined through the on-off of the left landing gear landing switch and the right landing gear landing switch and the speed state signal of the aircraft, the false alarm signal is avoided under the state thata main brake wheel lands and turns up when the aircraft landed, and the accuracy of the residual pressure alarm signal is improved.

Description

technical field [0001] The invention relates to the field of aircraft anti-skid braking systems, in particular to an aircraft braking system and a control method thereof which can prevent false outputs through an air residual pressure alarm. 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-b...

Claims

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Application Information

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IPC IPC(8): B64C25/42B64C25/44B60T13/68B60T13/74B60T17/22
CPCB64C25/42B64C25/44B60T13/68B60T13/74B60T17/22Y02T50/40
Inventor 刘忠平韩亚国董智超
Owner XIAN AVIATION BRAKE TECH
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