Stability Limits of Spinning Missiles with Attitude Autopilot

Abstract

Cr = control moment derivative coefficient, 1=rad C = static moment derivative coefficient, 1=rad C _ = damping moment derivative coefficient, s=rad IP, IQ = roll and lateral moment of inertia, kg m kr = dynamic gain of servo system ks = gain of servo system k! = gain of rate feedback kz = gain of attitude feedback L = reference length, m ncy, ncz = control command along Oy4 and Oz4 Ox5y5z5 = nonspinning velocity coordinate q = dynamic pressure, N=m S = reference area, m Ts = reciprocal of natural frequency of servo system, s = roll angle, rad c = coupling angle of the servo system, rad d = total delay angle of the system, rad l = lead angle of the command, rad m = roll angle measured by feedback element, rad = nutation angle, rad 2, 1 = nutation angle on plane Ox5y5 and plane Ox5z5, rad # = pitch angle, rad s = damping ratio of servo system cz, cy = command of servo in nonspinning body coordinate, rad 1, 2 = control surface angle in nonspinning body coordinate, rad = time delay of control system, s = yaw angle, rad