Paper shows that it appears possible to realize real-time optimal control by in-flight guidance computers; proposed method is discussed and illustrated by two examples; in case of arbitrary inclined flight, control variable can be expressed as function of state variables; in case of zero-lift flight control variable can be expressed as function of state variables and two unknown constants; constants can be determined by steep descent search in parameter space; modified method of steepest descent appears suitable for use by simple guidance computer. (In English with French and German abstracts)
Synthesis of real-time optimal controllers for rockets
Astronautica Acta
Astronautica Acta ; 12 , n 1
1966
7 pages
Article (Journal)
English
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Wiley | 2011
|NTRS | 1959
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|SLUB | 2002
|Engineering Index Backfile | 1949
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