This paper is a comparison between integral plus fuzzy logic control and LQR plus Hinfinity robust control as demonstrated on a flexible platform to improve space structure vibration control. Reusable launch vehicle components demand a micro-acceleration attenuation system, as opposed to stiffening these components at a tremendous weight cost. Also, these control systems are applicable to pointing/placing a payload in orbit. These systems will alleviate difficulties associated with the lack of an accurate pre-launch space structure dynamic model. An analysis of the open-loop characteristics of an isolated platform demands an investigation of both an integral plus fuzzy logic vibration controller and a robust vibration controller, an LQR inner loop and an Hinfinity outer loop. The benefits and limitations of these controllers are analyzed.
Flexible space structure robust vibration control
American Control Conference, 1999 ; 4378-4382
1999
5 Seiten, 7 Quellen
Conference paper
English
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