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Mixed airplane brake system and control method

A braking system and a hybrid technology, applied in the direction of aircraft braking arrangements, brake regulators, etc., can solve problems such as poor safety, and achieve the effects of easy troubleshooting and maintenance, ensuring safe use, and avoiding the effects of braking tires

Inactive Publication Date: 2013-06-19
XIAN AVIATION BRAKE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] In order to overcome the shortcomings of poor safety in the prior art, the present invention proposes a hybrid aircraft braking system and its control method

Method used

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Embodiment Construction

[0039] In this embodiment, the technical solution of the present invention is described in detail by taking the control of an aircraft main landing gear wheel as an example.

[0040] Such as figure 1 As shown, the brake valve 1 is installed under the cockpit floor, and is manipulated by the driver by depressing the brake pedal to output the required brake pressure. Brake valve 1 has three hydraulic pressure nozzles. The oil inlet of brake valve 1 is connected to the pipeline of the aircraft pressure supply system, the brake port of brake valve 1 is connected to the oil inlet pipeline of electro-hydraulic servo valve 2, and the oil return port of brake valve 1 passes through the aircraft oil return pipeline and the oil return tank Unicom.

[0041] The electro-hydraulic servo valve 2 has an electrical socket and three hydraulic interfaces. The electrical socket is electrically connected to the control box 7 through a cable with a plug, and receives the anti-skid control curren...

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Abstract

The invention relates to a mixed airplane brake system and a control method. A brake valve of the mixed airplane brake system is connected to a airplane pressure supply system, an electro hydraulic servo valve oil inlet and an oil returning tank through a pipeline; the electro hydraulic servo valve is connected to a brake nozzle of the brake valve, an oil inlet of the electromagnetic valve and an airplane oil return tube through the pipeline; and an electromagnetic hydraulic lock and the electro hydraulic servo valve are parallel channels on a hydraulic line. An oil inlet pressure transducer is arranged on the pipeline between the brake valve and the electro hydraulic servo valve; a brake port pressure transducer is arranged on the pipeline between the electromagnetic valve and a brake machine wheel. Under the failure of the electro hydraulic servo valve, an airplane antiskid brake control system can automatically convert a current normal brake mode to a standby brake mode and then enables reliable operation, driver intervention is not required, so that the work load of the driver is reduced. The mixed airplane brake system enables mode record on a fault state of the electro hydraulic servo valve, and is convenient for troubleshooting and maintenance by maintainer after flight.

Description

technical field [0001] The invention relates to an aircraft anti-skid brake control system and a control method, in particular to a hybrid aircraft brake system and a control method used when an electro-hydraulic servo valve fails. Background technique [0002] The aircraft wheel brake system is a component of modern aircraft landing gear, and is the basic guarantee equipment for the safe operation of aircraft take-off, landing roll and ground taxi control. Prevent punctured tires. The performance and reliability of the aircraft braking system are directly related to the safety of the aircraft. Electronic anti-skid brake control system is widely used in modern aircraft, and its basic composition includes four accessories of brake valve, speed sensor, control box and electro-hydraulic servo valve. The brake valve is a variable pressure reducer, which is controlled by the driver to reduce the hydraulic pressure provided by the pressure source to the required brake pressure, ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C25/46
Inventor 何永乐何文静
Owner XIAN AVIATION BRAKE TECH
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