The attitude control of an observation satellite, which exhibits highly uncertain lightly damped modes, is designed by loop-shaping H(sub infinity) design. Minimum-order controllers solving an LMI (Linear Matrix Inequality) formulation of the problem are sought, using a cone complementarity linearization algorithm. For different control laws, it is explained why the procedure leads to very low-order controllers. To analyze the stability robustness of the control law, different structured singular-value upper bounds and fitting characterizations of sets of uncertainties allow the computational cost of a mixed micro-analysis procedure to be minimized. Finally, the performance of the control law is studied on a nonlinear simulator.
Low-order robust attitude control of an earth observation satellite
Robuste Flugregelung eines Erdsatelliten mit niedriger Reglerordnung
Control Engineering Practice ; 7 , 4 ; 493-506
1999
14 Seiten, 18 Bilder, 1 Tabelle, 21 Quellen
Article (Journal)
English
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