Method for verifying internal leakage fault of aircraft brake valve

A verification method and brake valve technology, which is applied in the testing of mechanical components, testing of machine/structural components, testing of fluid tightness, etc., can solve problems such as the large gap between the valve core and valve sleeve, and save development resources and energy, eliminate internal leakage failure mode, and shorten the development cycle

Inactive Publication Date: 2015-08-05
XIAN AVIATION BRAKE TECH
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

[0007] 2. Due to the large matching gap between the valve core and the valve sleeve, there will be no sticking between the valve core and the valve sleeve caused by the volume change under the condition of temperature change, so there is no temperature change test content in the internal leakage verification

Method used

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  • Method for verifying internal leakage fault of aircraft brake valve
  • Method for verifying internal leakage fault of aircraft brake valve
  • Method for verifying internal leakage fault of aircraft brake valve

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Embodiment Construction

[0061] The brake valve of the aircraft brake system product of the present invention is a typical spring mass system, which is used to convert 210kg / Cm 2 The oil source pressure is converted to 140kg / Cm 2 brake pressure. The working principle is: when braking, the driver steps on the pedal, compresses the decompression spring, the spring force presses down the valve core, opens the oil inlet chamber, and makes the 210kg / cm 2 A part of the pressure oil enters the brake chamber and leads from the brake chamber to the brake wheel. The other part enters the pressure-sensing chamber through the oil hole inside the spool and acts on the bottom of the spool. When the pressure-sensing pressure at the bottom of the spool and the spring force reach a balance state, the spool moves to close the oil-inlet chamber.

[0062] The brake valve is composed of a spring assembly, slide valve assembly, sleeve assembly, housing, etc. During the assembly and debugging process, the spring force of ...

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Abstract

A method for verifying an internal leakage fault of an aircraft brake valve comprises the steps of determining a life test scheme of a brake valve according to the operating condition, performing life test according to the life test scheme, determining the specific scope of roughness and the specific scope of hardness of the fitting surface between a valve core and a valve sleeve according to life test data, and adding manufacturing parameters minimizing the cost to a design drawing. By adopting the method of the invention, the wear life of a slide valve in the using process can be prolonged, so that the internal leakage fault of the brake valve is eliminated, the brake valve can meet the regulated service life requirement, and the brake valve has a stopping brake function under the condition of neither adding a chock nor using a large pressure accumulator. The demand of leakage control is made on the brake valve. Through internal leakage control, the brake valve can achieve a stopping brake function under the condition of using neither a chock nor a large pressure accumulator. The specific requirements of internal leakage control are stipulated in a development contract of the brake valve.

Description

technical field [0001] The invention relates to the verification field of wear life of aircraft brake products, in particular to a verification method for internal leakage faults of aircraft brake valves. Background technique [0002] Internal leakage is a common failure of aircraft brake valves. Internal leakage refers to the failure of hydraulic oil to leak from the high-pressure chamber through the gap between the valve core and the valve sleeve to the oil return chamber, causing the brake pressure to drop. At home and abroad, for the pressure drop caused by the internal leakage of the brake valve, the method of supplementing the pressure with a large pressure accumulator is adopted, and the wheel is chocked on the parking position of the aircraft to prevent the aircraft from sliding on the ground. [0003] The aircraft braking system is designed with take-off line braking function, landing anti-skid braking function, ground turning difference braking function, and ground...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M13/00G01M3/00
Inventor 乔建军
Owner XIAN AVIATION BRAKE TECH
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