Stability Limits for the Velocity Orientation Autopilot of Rolling Missiles

In this paper, we derive the sufficient and necessary stability conditions for rolling missiles with velocity orientation autopilot. For mathematical derivation, linear time-invariant models are established. Structures of autopilot nonrolling introduced. addition, effects structure parameters on discussed. Furthermore, methods associated actuator dynamics, static decoupling presented to improve missiles. Numerical simulations conducted verify accuracy discussion. It is demonstrated that can guide missile design stabilization flight