Linear Quadratic Regulation Method for Supersonic Missile Flight Control System Design

摘要

In this brief paper, linear quadratic regulation (LQR) method with approximated angles of attack and sideslip, integrated states, and special controller realization configuration are proposed for designs of a supersonic skid-to-turn missile flight control system. Approximations for angles of attack and sideslip let all state variables of the plant are measurable and can be used in state feedback control design. Integrations of states with specified controller realizations configuration let the compensated plant have good tracking characteristics and against aerodynamic coupling at low frequencies while keeping robustness at middle frequencies found from LQR method. The realized configuration is similar to angles of attack and sideslip stabilized conventional well proven control configurations. The proposed method gets more information for controlling the considered system and close relation between conventional and modern flight control system design techniques.