Flexible space structure robust vibration control

This paper is a comparison between integral plus fuzzy logic control and LQR plus H_∞ 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 H_∞ outer loop. The benefits and limitations of these controllers are analyzed