2個のホイールによる人工衛星の姿勢制御
1998 年 34 巻 1 号 p. 34-40
詳細
1998 年 34 巻 1 号 p. 34-40
The feedback control of attitude changes for a spacecraft with two reaction wheels is considered in this paper. The method used here is to utilize the phenomenon that an attitude change occurs around an axis perpendicularly intersecting the wheel rotation axes when the two reaction wheels rotate simultaneously. A periodic feedback law is proposed for the three-axis control of spacecraft attitude. The validity of the law is verified by numerical simulations.
