Engineering Notes: Stability Limits of Spinning Missiles with Attitude Autopilot

摘要

In this paper, the sufficient and necessary condition of the coning motion stability of spinning missiles with attitude autopilots is analytically derived and further verified by the mathematical simulation on the nonlinear model. It is noticed that the stable region of the design parameters for the attitude autopilot shrinks so significantly due to the spinning of the missile that it is almost impossible to ensure the stability of an autopilot by means of the conventional method.