TY - JOUR
T1 - General attitude maneuvers of spacecraft with flexible structures
AU - Lin, Yiing Yuh
AU - Lin, Gern Liang
N1 - Funding Information:
This work was supported by the National Science Council of Taiwan under Grant NSC 80-0404-E006-19 and is gratefully acknowledged. The authors would also like to thank the anonymous reviewers, who made many crucial comments and suggestions to this paper.
PY - 1995/3
Y1 - 1995/3
N2 - An efficient composite control strategy is proposed in this paper permitting simultaneous multi-axis reorientation of a spacecraft with flexible structures. The proposed control, separating large and small motions of the dynamic system, includes three parts that can be independently designed and tuned. For each maneuver, an open-loop referencing attitude control trajectory is derived by considering the spacecraft as rigid and executed by part 1. Flexural deformations of the structures are stabilized by part 2. Part 3, encompassing part 1 and part 2 control results and external disturbances, is an optimal guidance that tracks part 1 reference trajectory and achieves the specified final attitude in finite time. Three simulation cases are included in which a flexible model spacecraft is used. Collocated actuators and sensors are placed on the hub and on the flexible structures of the spacecraft.
AB - An efficient composite control strategy is proposed in this paper permitting simultaneous multi-axis reorientation of a spacecraft with flexible structures. The proposed control, separating large and small motions of the dynamic system, includes three parts that can be independently designed and tuned. For each maneuver, an open-loop referencing attitude control trajectory is derived by considering the spacecraft as rigid and executed by part 1. Flexural deformations of the structures are stabilized by part 2. Part 3, encompassing part 1 and part 2 control results and external disturbances, is an optimal guidance that tracks part 1 reference trajectory and achieves the specified final attitude in finite time. Three simulation cases are included in which a flexible model spacecraft is used. Collocated actuators and sensors are placed on the hub and on the flexible structures of the spacecraft.
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U2 - 10.2514/3.21379
DO - 10.2514/3.21379
M3 - Article
AN - SCOPUS:0029273004
SN - 0731-5090
VL - 18
SP - 264
EP - 271
JO - Journal of Guidance, Control, and Dynamics
JF - Journal of Guidance, Control, and Dynamics
IS - 2
ER -