摘要
为了抑制压力波动,对完整飞行剖面下的液压系统工作状态进行分析.针对飞机液压系统提出流量负载模拟器原理,设计新型变速积分PI控制器,建立系统数学模型,确定各参数取值,开展数值仿真和试验研究,指出该流量负载模拟器的优缺点.仿真和试验结果均表明,在完整飞行剖面下,液压系统的可用压力在20.4 MPa以上,液压系统稳定可靠.相比于增量式PI控制器,采用变速积分PI控制器的压力波动至少减小了40%.
The working condition of an aircraft hydraulic system during the full flight phases was analyzed to reduce pressure fluctuation.The principle of flow load simulator was proposed for aircraft hydraulic system and the new variable integral PI controller was brought forward.The mathematic models of flow load simulator system were established and the value of each parameter was defined.Both the numerical simulation and test investigation were conducted,also the pros and cons of the simulator were pointed out.The simulation and test results show that during the full flight phases,the available pressure of an aircraft hydraulic system is always above 20.4MPa,which means that the flow capacity can meet the demand.The pressure fluctuation amplitude of the system with the developed PI controller is reduced by more than 40%compared to the traditional PI controller.
出处
《浙江大学学报（工学版）》
EI
CAS
CSCD
北大核心
2017年第6期1111-1118,共8页
Journal of Zhejiang University：Engineering Science
基金
国家自然科学基金资助项目(51675473)
浙江省重点科技创新团队(2013TD01)
关键词
飞机液压系统
流量负载模拟
变速积分
泵源
飞行剖面
PI控制器
aircraft hydraulic system
flow load simulator
variable integral
pump source
flight phases
PI controller
