Improving transient performance of dynamic inversion missile autopilot by use of backstepping

摘要

In this paper the backstepping design approach is used for a missile autopilot. The plant is separated into 2 subsystems, such that single controllers can be designed and therefor the stability of the entire system is reached automatically. Since the single laws are designed using the Nonlinear Dynamic Inversion, the similarity of the control laws to the 2-Timescale approach with Nonlinear Dynamic Inversion is shown. The main difference, being the analytic derivative of the inner control law, is used and this significantly improves the transient performance. This and how further improvements can be made by using the derivatives of the commanded trajectory is shown by simulation results.