Control laws for launch vehicles for large spacecraft were investigated by minimizing a quadratic performance index or by modal control. Parametric optimization methods were determined for a launch vehicle with bending; propellant sloshing was disregarded. A dynamic compensator is proposed based on modal control according to Pearson's method. The compensator was derived from simplified equations of the vehicle (without bending), and extended to the flexible vehicle in the presence of selective filters. This method can be extended to the whole vehicle and certain filtering problems may be eliminated. Calculations were based on the Diamant launch vehicle.
Control of Space Launchers
1973
45 pages
Report
Keine Angabe
Englisch
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