The invention discloses an aircraft hydraulic system. The aircraft hydraulic system comprises two sets of main hydraulic subsystems and a set of emergency hydraulic subsystem, and further comprises a two-way energy conversion device, a one-way energy conversion device and a control unit. The two-way energy conversion device is arranged between the two sets of main hydraulic subsystems and can selectively realize transmission of hydraulic energy between the two sets of main hydraulic subsystems. The one-way energy conversion device is arranged between one set of main hydraulic subsystem and the emergency hydraulic subsystem and can transmit hydraulic energy to the emergency hydraulic subsystem from the main hydraulic subsystem. The control unit can selectively start the two-way energy conversion device and the one-way energy conversion device according to the working conditions of pump sources in the two sets of main hydraulic subsystems and the emergency hydraulic subsystem. According to the aircraft hydraulic system and an aircraft, a relatively smaller electric driving pump can be adopted on the premise that the requirements of all hydraulic users are met, the power source load or the power source requirement of the hydraulic system is reduced, and the design difficulty and the configuration requirement are reduced.
本发明公开了一种飞机液压系统,该飞机液压系统包括两套主液压子系统和一套应急液压子系统,并且还包括:双向能源转化装置,其设置在两套主液压子系统之间并能够选择性地在两套主液压子系统之间实现液压能源的传输;单向能源转化装置,其设置在一套主液压子系统和应急液压子系统之间,并能够自该套主液压子系统向应急液压子系统传输液压能源;控制单元,其能够根据两套主液压子系统和一套应急液压子系统中的泵源的工作情况有选择地开启双向能源转化装置和单向能源转化装置。根据本发明的飞机液压系统及飞机,能够在满足各个液压用户的需求的前提下采用相对更小的电动驱动泵,并减少液压系统的电源负载或电源需求,降低设计难度和配置要求。
Aircraft hydraulic system and aircraft
飞机液压系统及飞机
2021-06-22
Patent
Electronic Resource
Chinese
European Patent Office | 2024
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