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Airplane hydraulic brake and nose wheel steering mechanism

A front wheel steering and aircraft hydraulic technology, which is applied to aircraft parts, control mechanisms, aircraft brake arrangements, etc., can solve problems such as liquid leakage, high heat generation, high temperature damage of hydraulic pumps, etc., and achieve the effect of eliminating pressure pulsation

Active Publication Date: 2014-05-28
HARBIN
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AI Technical Summary

Problems solved by technology

The existing aircraft wheel brakes are continuously supplied by the hydraulic pump to the hydraulic system. The aircraft hydraulic brake mechanism using this mechanism generates a lot of heat, which is likely to cause high temperature damage to the hydraulic pump or liquid leakage.

Method used

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  • Airplane hydraulic brake and nose wheel steering mechanism

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Embodiment Construction

[0011] The present invention will be described in further detail below. see figure 1 , the aircraft hydraulic brake mechanism includes, hydraulic oil tank 1, low oil level detector 2, two hydraulic pumps 3, one-way valve 4, oil filter 5, safety valve 6, unloading valve 7, pressure accumulation one-way valve 8, brake Pressure accumulator 9, air pressure gauge 10, inflation nozzle 11, pressure sensor 12, pressure switch 13, brake distribution valve 14, anti-skid solenoid valve 15, anti-skid throttle valve 16, brake wheel 17, brake control pedal 18, front wheel Turn Actuator 19. The hydraulic oil tank 1 is connected to the low oil level detector 2, the two outlets of the hydraulic oil tank 1 are respectively connected to one end of two hydraulic pumps 3, and the other ends of the two hydraulic pumps 3 are connected to one end of the check valve 4 at the same time , the other end of the one-way valve 4 is connected with the safety valve 6, the unloading valve 7 and the pressure ...

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Abstract

The invention belongs to the technical field of airplane hydraulic control and relates to an airplane hydraulic brake mechanism for providing hydraulic energy for the brake wheel and nose wheel steering actuator of an airplane. The mechanism comprises a hydraulic oil tank (1), a low oil-level detector (2), two hydraulic pumps (3), a check valve (4), an oil filter (5), a safety valve (6), an unloading valve (7), an accumulating check valve (8), a brake accumulator (9), a barometer (10), an air charging nozzle (11), a pressure sensor (12), a pressure switch (13), a brake distribution valve (14), an anti-slip electromagnetic valve (15), an anti-slip throttle valve (16), the brake wheel (17) and a brake control pedal (18). The mechanism has the advantages as follows: a heating problem because the hydraulic pumps of the airplane provide pressure continuously for the brake wheel and the nose wheel steering actuator of an undercarriage can be effectively eliminated, and pressure pulses produced by continuous pressure supply can be simultaneously eliminated; the long-term reliable and stable work requirements of the airplane brake system are met.

Description

technical field [0001] The invention belongs to the technical field of aircraft hydraulic control, and relates to an aircraft hydraulic brake mechanism that provides hydraulic energy for aircraft brake wheels and front wheel steering actuators. Background technique [0002] Aircraft wheel braking and nose wheel steering is an important function that an aircraft performs on the ground. Existing aircraft wheel brakes are continuously supplied by a hydraulic pump to the hydraulic system. The aircraft hydraulic brake mechanism using this mechanism generates a large amount of heat, which is likely to cause high-temperature damage to the hydraulic pump or liquid leakage. The invention utilizes the intermittent pressure supply design of the hydraulic pump to reduce the overall calorific value of the hydraulic brake mechanism of the aircraft, so that the aircraft can perform smooth and reliable braking and front wheel turning on the ground. Contents of the invention [0003] The ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C25/44B64C25/50
Inventor 杜荃朱博项滨东刘春艳谷峰王洪志张卓然杨晓亮贾国良
Owner HARBIN
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