Robust Dynamic Inversion Flight Control Law Design

In order to solve the robustness problem of regular explicit nonlinear dynamic inversion (NDI) control law, the incremental version NDI control law is designed via the implicit dynamic inversion (DI) method and singular perturbation theory, in which the state acceleration (derivative) is feedback to measure the effects of the aircraft model perturbation and the current position information of the effector is needed. The whole aerodynamic model is unnecessary because there is no nonlinear direct state feedback base on the nominal aircraft model, and as a result, the sensitivity to aircraft model is decreased. The control structure is simple, re-allocation of control power and the reconfiguration of control law can be achieved conveniently and rapidly. The control law design and computer simulation for an aircraft with aerodynamic perturbation demonstrate that the robustness of the control law is increased.