Computer efficient determination of optimum performance ascent trajectories

A pitch program has been designed wherein a pitch rate equation is used as a function of time to approximate the general characteristics of the step pitch program usually used in the early part of vehicle ground-to-orbit flight. The computer time and engineering time required for the pitch program development using the pitch rate equation are shown to be significantly less than for the gravity-turn method and much less than for complete optimization. The proposed program yields an essentially maximum payload.