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