摘要
建立了航空发动机喷口-压比线性模型和喷口执行机构数学模型,在此基础上对航空发动机压比控制系统展开研究,设计了三个回路的控制方式。对分油活门位移和作动筒活塞位移分别设计了PI控制和比例控制的内闭环,针对压比采用PID控制,并分别整定了各控制器的参数。仿真表明,该压比闭环控制系统在包线内控制压比效果良好,控制系统鲁棒性强。
A three--loop control method was designed for aero--engine pressure ratio controlsystem based on the linear model of aircraft engine and model of nozzle actuator.PI control and P control algorithms were designed for displacement of the fuel--valve and the actuating cylinder loops. PlD control algorithm was designed for pressure ratio control loop. Simulation on a turbofan engine shows robust property of the pressure ratio control system with three--loop structure.
出处
《科技资讯》
2012年第1期119-124,共6页
Science & Technology Information
