In this paper, we study the stabilization problem of a spacecraft with three independent torque actuators via state feedback. We describe its attitude with the quaternion q_??_(q1, q2, q3, q4), ||q||2_??_q12+q22+q32+q42=1, instead of the rotation matrix R∈SO(3), which is known to have the manifold structure. The purpose of this paper is to derive a global static feedback law such that quaternion q
361 66 361 - 3742016 2015 3 31 2015 7 22 *e-mail: hiroki@affrc.go.jp * A comparison of softwares for state space models Hiroki Itô* Forestry and Forest Products Research Institute d lmK FASB UGS S tan d lm KFAS R d lm K FAS dlm M CMC B UGS M CMC WinBUGSO penBUGSJ AGS S tan S tan gaussian_dlm_obs g aussian_dlm_obs B UGS Stan d lm KFAS BUGSdlmKF ASRStan 特集 2 Commandeur and Koopman 2007 2016 2016 C o
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