Attitude recovery for microsatellite via magnetic torque

The problem of the attitude recovery via three orthogonal magnetic torquers solely for a moment-biased microsatellite is investigated. Three orthogonal magnetic torquers are innovatively used to detumble the microsatellite and then recover the attitude. Feedback linearization method is adopted to obtain the linear attitude dynamics. Based on the linearization model a quasi PD controller is designed, meanwhile ¿-synthesis control theory is adopted to synthesis the robust controller. The performance and robustness of the two type controllers are compared with the classical PD controller in a magnetic storm simulation scenario. The robustness superiority of the ¿-synthesis controller over classical PD and quasi PD controllers is obviously.