Integrated guidance and control for a missile in the pitch plane based upon subspace stabilization

Based upon the model of the relative motion between the missile and the target and the model of the missile moving in the pitch plane, a novel integrated guidance and control model under the error tracking meaning is established. It is different from the state equation based integrated guidance and control models, it emphasizes particularly on attitude angles tracking. Especially, the realization of the error tracking properties is turned into the corresponding parameters adjusting by subspace stabilization technology. The globally asymptotical stabilization of the error tracking system is realized by an observer with the adaptive adjusting function about the model error and about the target maneuverability. The simulation results indicate that the design is effective.