Various techniques for devising control law to steer rocket vehicle to thrust termination are discussed; consistent with present practice in space vehicle design, rational scheme is sought for relaxing constraints at thrust termination; introducing geometrical interpretation of optimality, "least-Squares" control scheme is obtained; it is shown that control scheme is stable at final time, and relationship to well-known velocity-to-be-gained steering scheme is pointed out; example of ascent guidance into near-earth satellite orbit is presented and simple technique for approximating optimal control law suggested.
Technique for optimal final value control of powered flight trajectories
AIAA J
AIAA Journal ; 4 , n 2
1966
9 pages
Article (Journal)
English
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