ATTITUDE AND VIBRATION CONTROL FOR A FLEXIBLE SPACECRAFT WITH DOUBLE-GIMBAL VARIABLE-SPEED CONTROL MOMENT GYROS

被引：0

作者：

Sasaki, Takahiro ^{[1
,2
]}

Shimomura, Takashi ^{[1
]}

Pullen, Sam ^{[3
]}

Schaub, Hanspeter ^{[4
]}

机构：

[1] Osaka Prefecture Univ, Dept Aerosp Engn, Naka Ku, 1-1 Gakuen, Sakai, Osaka 5998531, Japan

[2] Univ Colorado, Dept Aerosp Engn Sci, ECNT 321,431 UCB, Boulder, CO 80309 USA

[3] Stanford Univ, Dept Aeronaut & Astronaut, Durand Bldg,Room 250, Stanford, CA 94305 USA

[4] Univ Colorado, Dept Aerosp Engn Sci, Engn, ECNT 321,431 UCB, Boulder, CO 80309 USA

来源：

THIRD IAA CONFERENCE ON DYNAMICS AND CONTROL OF SPACE SYSTEMS 2017 | 2017年 / 161卷

关键词：

D O I：

暂无

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The attitude and vibration control of a flexible spacecraft with two parallel double-gimbal variable-speed control moment gyros (DGVSCMGs) is considered. The coupled nonlinear equations of motion create a complex challenge in a pointing control development. First a Gain-Scheduled (GS) controller for a 3 axis attitude control is designed by the post-guaranteed linear matrix inequalities (LMIs) method with H-2/H-infinity constraints. Next an H-2/H-infinity, controller for vibration control is designed to attain both attitude and vibration control at the same time. The two controllers are combined using the dynamic inversion (DI) technique. Finally, the effectiveness of the proposed combined controller is demonstrated through a numerical example.

引用

页码：33 / 52

页数：20

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