Integrated versus two-loop guidance-autopilot for a dual control missile with high-order aerodynamic model

Abstract

This paper proposes a novel integrated guidance and autopilot design scheme for endo-atmospheric missiles having forward and rearward aerodynamic controls. The missile aerodynamic, including the aero-coupling effects between the canard and tail sections, is assumed to be non-linear. The value of the integrated design scheme is that it is solved in finite-time horizon to target interception, while maintaining missile angle of attack, canard and tail incidence angles within their aerodynamic limitations. The integrated design includes a feed-forward command generator based on the dual control missile trim conditions. The proposed design scheme is compared against a two-loop approach. The test cases via simulations are promising, achieving reduced control efforts and lower miss distances with the integrated logic.