Abstract:

A systematic design method for flight trajectory command integrated tracker of tactical mission integrated flight management system(TMIFMS) is developed through the multiple time scale singular perturbation method combined with dynamic inverse decoupling control theory and optimal decoupling control law theory for optimal linearization system in a small neighborhood of a dynamic equilibrium point. A controller for F 15 fighter is designed with the method. The results of digital simulation show that the controller can control fighter track commands in different time scales.

Key words: singular perturbation theory, linearization, optimization, nonlinear decoupling control, flight management system