Stability Limits of Spinning Missiles with Attitude Autopilot

摘要

AS ONE of the typical autopilots, the attitude autopilot cannstabilize static unstable airframes, improve control responses,nand maintain constant flight parameters. This type of autopilot hasnbeen widely applied in missiles attacking static or low-speed targets.nThe stability and design of the attitude autopilot have been discussednextensively for nonspinning missiles.However, for spinning missiles,nthis autopilot may be dynamically unstable in the form of a divergentnconning motion due to the existence of cross-coupling effects. Therefore,nthe stability boundary of an autopilot applicable to a nonspinningnmissile is no longer valid in the event of spinning. This problem hasnbeen indicated in our previous paper on the stability boundary of thenconing motion for spinning missiles with damping loops [1]. In thisnpaper, we focus on the quantitative description of the stability limitsnassociated with the attitude autopilot for spinning missiles.