Stability of Spinning Missiles with an Acceleration Autopilot

noticed that the stable region of the design parameters for the autopilot shrinks significantly under the spinning condition. It is also observed that the stable region for design parameters is further narrowed when an integrator is introduced into the acceleration loop while the steady-state accuracy is dramatically improved. A simple decoupling method of setting a lead angle for the commands to the servosystem is demonstrated to be effective to correct the crosscoupling and to extend the stability region for design parameters of the autopilot.

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