Nonlinear Stability Region Determination of Pilot-Aircraft Closed-Loop Based on Differential Manifold Theory

To deal with the severely flight safety problem for the modern high gain civil transport aircraft caused by instability, which affected by the activated actuator rate saturation, the stability region of pilot-aircraft closed-loop system was studied. Taking actuator rate saturation into account, a nonlinear pilot-aircraft closed-loop dynamic model was established. Through introducing manifold theory, the accuracy stability region of the system has been obtained. The validity and accuracy of the method were proved by validity verification and dynamic simulation. What’s more, the influence of different pilot-gain values and rate-limited values on the stability region was studied. The research results can be applied to flight safety risk assessment and provide theoretical guidance for design of flight control system.