Results indicate that guidance logic is relatively insensitive to mission energy or to residual errors from midcourse guidance that has a predictable effect on velocity-increment requirements. The guidance scheme is, however, sensitive to the altitude of the target perigee. Low-altitude targets are more accurately attained than those at higher altitude. A large range of 8 measurement errors is considered, and use of the radar-gyroscopic system is considered feasible for guidance to atmospheric-drag deceleration accuracies with instruments of current performance expectations.nA strong trend toward heavily "restrained" and "damped" guidance systems is indicated, and a large number of corrections in trajectory following initiation of guidance at long range would be desired. It is indicated that active control with no cutoff is preferred. Control
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