A method of removing hydraulic fluid from an aircraft hydraulic system. The hydraulic system comprises a hydraulic actuating mechanism which is actuated by an electro-hydraulic servo valve; a hydraulic fluid port through which hydraulic fluid can escape; and a hydraulic fuse having a closed state and an open state, the hydraulic fuse being between the electro-hydraulic servo valve and the hydraulic fluid port. The hydraulic fluid port is opened, and then activation of the electro-hydraulic servo valve is controlled to force hydraulic fluid to escape from the hydraulic system via the hydraulic fluid port, the control being such that the hydraulic fuse does not enter and remains in a closed state.
一种将液压流体从飞行器液压系统移除的方法。该液压系统包括:液压致动机构,该液压致动机构通过电液伺服阀致动;液压流体端口,液压流体可以通过该液压流体端口逸出;和具有关闭状态和打开状态的液压熔断器,该液压熔断器在电液伺服阀与液压流体端口之间。打开液压流体端口,以及然后控制电液伺服阀的启用,以迫使液压流体经由液压流体端口从液压系统逸出,所述控制使得液压熔断器不会进入并保持处于关闭状态。
Method of removing hydraulic fluid from aircraft hydraulic system, aircraft hydraulic system and aircraft
将液压流体从飞行器液压系统移除的方法、飞行器液压系统和飞行器
2022-06-10
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen |
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