Stability of multi-axis attitude maneuver of flexible spacecraft using hybrid control

Yiing Yuh Lin; Gern Liang Lin

doi:10.2514/6.1992-4449

Stability of multi-axis attitude maneuver of flexible spacecraft using hybrid control

Yiing Yuh Lin, Gern Liang Lin

Research output: Contribution to conference › Paper › peer-review

Abstract

The optimal control and stability problem of reorienting a flexible spacecraft is studied for the case of simultanuous multi-axis attitude maneuver. A multi-level control strategy is proposed which tracks a predetermined optimal attitude trajectory and suppress the flexible structure deformations at the same time. The multi-level integrated control consists of a three-part control efforts. An optimal open-loop rigid-body reference trajectory is obtained from iterative procedures. An output observer feedback control is used as local control to stabilize the flexible beams. Guidance law takes the system to the desired final attitude by following the optimal trajectory. Control stability is considered on the input disturbances effects.

Original language	English
Pages	227-234
Number of pages	8
DOIs	https://doi.org/10.2514/6.1992-4449
Publication status	Published - 1992
Event	Astrodynamics Conference, 1992 - Hilton Head Island, United States Duration: 1992 Aug 10 → 1992 Aug 12

Other

Other	Astrodynamics Conference, 1992
Country/Territory	United States
City	Hilton Head Island
Period	92-08-10 → 92-08-12

All Science Journal Classification (ASJC) codes

Astronomy and Astrophysics

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10.2514/6.1992-4449

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@conference{0fa6c26bde4e4dd19c8b732100497f12,

title = "Stability of multi-axis attitude maneuver of flexible spacecraft using hybrid control",

abstract = "The optimal control and stability problem of reorienting a flexible spacecraft is studied for the case of simultanuous multi-axis attitude maneuver. A multi-level control strategy is proposed which tracks a predetermined optimal attitude trajectory and suppress the flexible structure deformations at the same time. The multi-level integrated control consists of a three-part control efforts. An optimal open-loop rigid-body reference trajectory is obtained from iterative procedures. An output observer feedback control is used as local control to stabilize the flexible beams. Guidance law takes the system to the desired final attitude by following the optimal trajectory. Control stability is considered on the input disturbances effects.",

author = "Lin, {Yiing Yuh} and Lin, {Gern Liang}",

note = "Funding Information: This work was supported by the National Science Council research grant NSC 81-0401-E-006-38.; Astrodynamics Conference, 1992 ; Conference date: 10-08-1992 Through 12-08-1992",

year = "1992",

doi = "10.2514/6.1992-4449",

language = "English",

pages = "227--234",

}

TY - CONF

T1 - Stability of multi-axis attitude maneuver of flexible spacecraft using hybrid control

AU - Lin, Yiing Yuh

AU - Lin, Gern Liang

N1 - Funding Information: This work was supported by the National Science Council research grant NSC 81-0401-E-006-38.

PY - 1992

Y1 - 1992

N2 - The optimal control and stability problem of reorienting a flexible spacecraft is studied for the case of simultanuous multi-axis attitude maneuver. A multi-level control strategy is proposed which tracks a predetermined optimal attitude trajectory and suppress the flexible structure deformations at the same time. The multi-level integrated control consists of a three-part control efforts. An optimal open-loop rigid-body reference trajectory is obtained from iterative procedures. An output observer feedback control is used as local control to stabilize the flexible beams. Guidance law takes the system to the desired final attitude by following the optimal trajectory. Control stability is considered on the input disturbances effects.

AB - The optimal control and stability problem of reorienting a flexible spacecraft is studied for the case of simultanuous multi-axis attitude maneuver. A multi-level control strategy is proposed which tracks a predetermined optimal attitude trajectory and suppress the flexible structure deformations at the same time. The multi-level integrated control consists of a three-part control efforts. An optimal open-loop rigid-body reference trajectory is obtained from iterative procedures. An output observer feedback control is used as local control to stabilize the flexible beams. Guidance law takes the system to the desired final attitude by following the optimal trajectory. Control stability is considered on the input disturbances effects.

UR - http://www.scopus.com/inward/record.url?scp=85007256334&partnerID=8YFLogxK

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U2 - 10.2514/6.1992-4449

DO - 10.2514/6.1992-4449

M3 - Paper

AN - SCOPUS:85007256334

SP - 227

EP - 234

T2 - Astrodynamics Conference, 1992

Y2 - 10 August 1992 through 12 August 1992

ER -

Stability of multi-axis attitude maneuver of flexible spacecraft using hybrid control

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