Robust control and limit protection in aircraft gas turbine engines

摘要: Uncertainties and, in particular, large inlet distortions, affect closed-loop stability, performance, and erode surge margins of aircraft gas turbine engines. Traditional robust control techniques can be combined with reference governors to preserve the stability tracking while enforcing margin constraints. The paper examines uncertainty modeling, effect distortions on engine controller architecture selection; it also illustrates application governor H-infinity controller. Our results suggest that performance feedback loop maintained techniques, hence constraint handling (limit protection) represents primary goal dealing distortions.