Bank-to-turn missiles develop their steering force by banking to orient the aerodynamic normal force in the direction commanded by the guidance law. The design of autopilots for such missiles is a challenge because the order of the dynamic model is relatively high and all the axes are coupled. The coupling of the pitch and yaw axes, moreover, due to coriolis and gyroscopic effects, is significant and nonlinear. A method based on linear-gaussian-quadratic control theory makes use of the 'adiabatic approximation' to deal with cross-coupling between the pitch and yaw axes of the missile proportional to roll rate. A software package has been developed to perform all the required design calculations, performance evaluation, and robustness assessment. This software has been used for the design of autopilots for several prospective airframes with results that achieve desired performance objectives. The control architecture is unlike that which a classical design would achieve, but performance of the two designs are comparable. Keywords: Attitude control systems: Turning flight; Control theory. (EDC)


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