Results are presented to illustrate the application of established procedures of linear, quadratic, Gaussian optimal estimation and control to a spacecraft with dynamically significant elastic appendages. Interpretations are provided in both time domain and frequency domain, and conclusions are drawn for a wide class of problems of flexible spacecraft attitude control.
An application of modern control theory to an elastic spacecraft
1976-01-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
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