The invention relates to the technical field of aircrafts, in particular to a redundancy hydraulic control system of an aircraft undercarriage. In order to solve the emergency risk problem that a hydraulic retractable system cannot act due to driving faults, the hydraulic retractable system comprises a hydraulic driving unit, an oil tank, a reversing valve, an undercarriage actuating cylinder and a pneumatic emergency unit, an outlet of the hydraulic pump is connected with a first opening of the reversing valve; the undercarriage actuating cylinder is provided with a put-down cavity and a put-up cavity; the lower cavity and the upper cavity are both connected with the reversing valve; the pneumatic emergency unit comprises a gas cylinder, a switch valve, a shuttle valve and a pneumatic one-way valve; the shuttle valve is provided with a first shuttle valve inlet, a second shuttle valve inlet and a shuttle valve outlet, the gas cylinder is connected with the first shuttle valve inlet through the switch valve, the second shuttle valve inlet is connected with a second opening of the reversing valve, and the shuttle valve outlet is connected with the laying-down cavity; the pneumatic control one-way valve is connected with the end, away from the gas cylinder, of the switch valve and connected with the upper collecting cavity.
本发明涉及飞行器技术领域,尤其涉及一种飞行器起落架的余度液压控制系统。为了解决液压收放系统则存在驱动因驱动故障导致收放系统无法动作的紧急风险问题,本发明的技术方案包括液压驱动单元、油箱、换向阀、起落架作动筒和气动应急单元;液压泵的出口与换向阀的第一口相连接;起落架作动筒具有放下腔和收上腔;放下腔和收上腔均与换向阀相连接;气动应急单元包括气瓶、开关阀、梭阀和气控单向阀;梭阀具有第一梭阀入口、第二梭阀入口和梭阀出口,气瓶通过开关阀与第一梭阀入口相连接,第二梭阀入口与换向阀的第二口相连接,梭阀出口与放下腔相连接;气控单向阀与开关阀远离气瓶的一端相连接,气控单向阀与收上腔相连接。
Redundancy hydraulic control system of aircraft undercarriage
一种飞行器起落架的余度液压控制系统
2024-02-02
Patent
Electronic Resource
Chinese
British Library Conference Proceedings | 1997
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