A DOUBLE LOOPS CONTROLLER DESIGNMETHOD FOR LARGE FLEXIBLE SPACECRAFT

LIU Chunmei; SHEN Yi; HU Hengzhang

doi:10.11728/cjss1999.02.181

Volume 19 Issue 2

Apr. 1999

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Article Navigation > Chinese Journal of Space Science > 1999 > 19(2): 181-186

LIU Chunmei, SHEN Yi, HU Hengzhang. A DOUBLE LOOPS CONTROLLER DESIGNMETHOD FOR LARGE FLEXIBLE SPACECRAFT[J]. Chinese Journal of Space Science, 1999, 19(2): 181-186. doi: 10.11728/cjss1999.02.181

Citation:

LIU Chunmei, SHEN Yi, HU Hengzhang. A DOUBLE LOOPS CONTROLLER DESIGNMETHOD FOR LARGE FLEXIBLE SPACECRAFT[J]. Chinese Journal of Space Science, 1999, 19(2): 181-186. doi: 10.11728/cjss1999.02.181

LIU Chunmei, SHEN Yi, HU Hengzhang. A DOUBLE LOOPS CONTROLLER DESIGNMETHOD FOR LARGE FLEXIBLE SPACECRAFT[J]. Chinese Journal of Space Science, 1999, 19(2): 181-186. doi: 10.11728/cjss1999.02.181

Citation:

LIU Chunmei, SHEN Yi, HU Hengzhang. A DOUBLE LOOPS CONTROLLER DESIGNMETHOD FOR LARGE FLEXIBLE SPACECRAFT[J]. Chinese Journal of Space Science, 1999, 19(2): 181-186. doi: 10.11728/cjss1999.02.181

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A DOUBLE LOOPS CONTROLLER DESIGNMETHOD FOR LARGE FLEXIBLE SPACECRAFT

doi: 10.11728/cjss1999.02.181 cstr: 32142.14.cjss1999.02.181

Department of Control Engineering, Harbin institute of Technology, 150001

Received Date: 1997-10-28
Rev Recd Date: 1999-01-25
Publish Date: 1999-04-24

Abstract

Abstract

In this paper, a double loops controller design method is provided in accordancewith the characteristics of large flexible spacecraft, such as low frequency, low damping and coupling between rigid body and flexible appendages. Optimal sliding-modecontrol method is used, and robust stability is considered. Finallyg numerical simulations show that vibration suppression and accurate pointing are accomplishedby using two separate control loops with certain robust property. Based on modetruncation modle of the flexible spacecraft.
- Double loops,
- Acceleration feedback,
- Optimal sliding-mode,
- Variable structure