The development of the gradient technique, for trajectory optimization has made it possible to determine rapidly the thrust-attitude history that maximizes the performance of a rocket booster. However, it would be unnecessarily complicated to design a booster autopilot to follow the exact optimum thrust-attitude history. To simplify the autopilot, many boosters are limited to a tilt program that is composed of constant-pitch-rate segments. The approach suggested in this note is to fit a linear-segment curve to the nonlinear thrust-attitude history that is obtained from the optimization program. (Author)
Rapid Determination of Near-Optimum Linear Pitch Programs for Rocket Boosters
1967
3 pages
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Englisch