Control Analysis and Autopilot Design for Static Unstable Missiles

The static stability feature of missile airframe due to varied parameter, The characteristics and benefit of applying relaxed static stability technology on missile flight performance were analyzed. The technologies transforming time-domain and frequency-domain mixed performance indexes into desired poles, as well as state feedback into output feedback were derived respectively. In view of different autopilot topologies, Anyone of the two- and three-loop autopilots can stabilize a static unstable missile. Finally, a general there-loop autopilot design procedure based on pole assignment and optimization was proposed. The analysis and simulation results show that static unstable missiles can be stabilized by a three-loop topology autopilot. However, the finite resource of actuator is the crucial limit factor dominating autopilot function, and proper distance from accelerometer to missile gravity center is benefit to improve system stability.