CSVS Method for Spacecraft with Two Flexible Appendages during Attitude Maneuver

Guan Yu Wang; Wei Ping Ge; Guang Wei Yang; Sheng Chao Wang

doi:10.4028/www.scientific.net/AMR.1049-1050.939

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HomeAdvanced Materials ResearchAdvanced Materials Research Vols. 1049-1050CSVS Method for Spacecraft with Two Flexible...

CSVS Method for Spacecraft with Two Flexible Appendages during Attitude Maneuver

Abstract:

An angle maneuver control strategy of spacecraft with two flexible appendages based on component synthesis vibration suppression (CSVS) method is put forward. Unwanted flexible vibration modes can be eliminated while desired rigid motion can be achieved by this method. Jet device and Momentum wheel system are used as the actuator of the spacecraft’s angle maneuver. Several time-fuel control strategies are designed for spacecraft with flexible appendages. Simulation results validate the feasibility of the CSVS method. The DC motor control method is researched in order to combine momentum wheel system with CSVS method.

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Periodical:

Advanced Materials Research (Volumes 1049-1050)

Pages:

939-944

DOI:

https://doi.org/10.4028/www.scientific.net/AMR.1049-1050.939

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Online since:

October 2014

Authors:

Guan Yu Wang, Wei Ping Ge, Guang Wei Yang, Sheng Chao Wang

Keywords:

Component Synthesis Vibration Suppression (CSVS) Method, Large Angle Maneuver, Multi-Deformable-Body Dynamics

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References

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DOI: 10.3901/cjme.2001.03.224

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