Design and Validation of Aeroengine Control System with Non-fully Recovering LQG/LTR Method

A method of non-fully recovering LQG/LTR (linear quadratic Gaussian synthesis with loop transfer recovery) was introduced in the paper for solving the problem of over large values of the parameters in the conventional LQG/LTR controller. After the theory and the approach of non-fully recovering LQG/LTR were introduced, this method was applied to design the aeroengine control system. The research result showed that the values of non-fully recovering LQG/LTR controller parameters can be reduced effectively and without any capability loss of the control system compared with the controller designed by conventional LQG/LTR methodology. In order to validate the performance of the designed control system, the hardware-in-the-loop simulation system was designed from hardware and software, and then the hardware-in-the-loop simulation of the control system in the flight envelope has been performed. Excellent robustness and anti-disturbance properties of the controller are obtained, and the demands of multivariable control of aeroengine are reached from the simulation result. So, it is verified that the Non-fully recovering LQG/LTR methodology is suitable for the design of areoengine multivariable controller, the designed hardware-in-the-loop simulation system can simulate the aeroengine and the engine controller´s work process effectively.