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A landing gear and front landing gear technology, applied in the chassis and other directions, can solve the problems of high power and heavy weight required for the hydraulic retraction of the landing gear, and achieve the effects of high reliability, simple energy saving, cost reduction, and reduced power consumption
Active Publication Date: 2022-01-11
中电科芜湖通用航空产业技术研究院有限公司 +1
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[0005] The purpose of the present invention is to provide a hydraulic retractable landing gear mechanism, which solves the problems of high power and heavy weight required for hydraulic retractable landing gear
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[0012] The present invention will be described in further detail below in conjunction with the accompanying drawings.
[0013] combine figure 1 , a hydraulically retractable landing gear mechanism according to the present invention, comprising a hydraulic pump 1, a hydraulic oil tank 2, a first one-way valve 3, a safety valve 4, a pressure accumulating regulating valve 5, an accumulating one-way throttle valve 6, Pressure accumulator 7, pressure relay 8, second one-way valve 9, third one-way valve 10, unloading valve 11, fourth one-way valve 12, first two-position two-way solenoid valve 13, second two-position two-way Through electromagnetic valve 14, the fifth one-way valve 15, emergency release two-position two-way valve 16, travel switch 17, emergency release cam disc 18, main landing gear hydraulic actuator 22, front landing gear hydraulic actuator 23 and main Landing gear retractable cylinder 24, three sixth one-way valves 19 and three groups of control valve groups, eac...
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Abstract
The invention discloses a hydraulic retractable landing gear mechanism, which comprises a hydraulic pump, a hydraulic oil tank, a first one-way valve, a safety valve, a pressure accumulation regulating valve, a pressure accumulation one-way throttle valve, a pressure accumulator, a pressure relay, a first Second one-way valve, third one-way valve, unloading valve, fourth one-way valve, first two-position two-way solenoid valve, second two-position two-way solenoid valve, fifth one-way valve, emergency discharge two-position two-way Through valve, travel switch, emergency lowering cam disc, main landing gear hydraulic actuator, nose landing gear hydraulic actuator and main landing gear retractable actuator, three sixth one-way valves and three sets of control valve groups. The invention can effectively reduce the power of the hydraulic energy source and has dual emergency lowering modes, is simple to operate and has higher reliability, and ensures that the landing gear of the aircraft can be lowered and landed safely.
Description
technical field [0001] The invention belongs to the technical field of aircraft hydraulic control, and in particular relates to a hydraulic retractable landing gear mechanism. Background technique [0002] The landing gear is a device used to support the weight of the aircraft and absorb the impact load when the aircraft is parked, taxiing, taking off and landing on the ground. It is a key component that affects the safety of the aircraft's take-off and landing. The retractable landing gear can significantly reduce the aerodynamic force of the aircraft. Drag, improving aerodynamic performance, is a common configuration for modern manned and unmanned aircraft. The design of the aircraft requires that the landing gear can be lowered under any reasonably possible failure of the retractable system to ensure the safe landing of the aircraft. [0003] 201811634425.2 discloses a "Aircraft Landing Gear Retractable Hydraulic System", which uses a motor-driven hydraulic pump as the h...
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