基于电液伺服控制燃油泵的航空发动机控制与仿真

为探索轻质化燃油系统结构，基于电调燃油变量泵的航空发动机转速控制系统，构建了柱塞泵斜盘位置电液伺服控制系统，油泵出口燃油直接输入电液伺服阀；建立了电液伺服阀线性化模型。通过数字仿真，研究了电液伺服阀工作特性，并得到了其适应性模型；在航空发动机特性半物理试验系统上，对斜盘位置电液伺服控制系统实物进行了验证试验，并与航空发动机模型一起构成了发动机转速闭环控制系统。结果表明：变输入压力的燃油电液伺服位置控制系统有效可行，变量泵工作稳定可靠，电液伺服阀模型能够准确反映实际工作状况；基于变参数PI控制算法的转速闭环控制初步取得成效。

Aero Engine Control and Simulation Based on Electro-hydraulic Servo Controlled Variable Stroke Plunger Pump

The research focuses on lighting the aero turbo-engine control system, which consists of a variable stroke axial plunger pump controlled by an electro-hydraulic servo position control system. Firstly, a mathemat- ical model of electro-hydraulic servo-valve is built and the performances have been simulated while the supply pressure varied in 3~8 MPa. Then an electro-hydraulic servo controlled variable pump system is built based on the reconstruction of plunger pump equipped originally with mechanic-hydraulic servo control unit. The control algorithm for the swash plate position is designed and validated by experimentation. Finally, combining the shaft speed and the swash plate position control system, the turbo engine simulation is carried out with the hardware in the loop. The result shows that the electro-hydraulic servo controlled pump works effectively. The engine is controllable by using variable parameters PID algorithm. It is proved practicable that the fuel is pumped directly to the servo valve in the construction of the fuel control system. Thus the structure of the fuel control system is simplified and hereby the engine performance improved.