Attitude Dynamics and Control of Spacecraft with Multiple Liquid Propellant Tanks
Publication: Journal of Aerospace Engineering
Volume 29, Issue 6
Abstract
This paper focuses on the dynamics and control of spacecraft with multiple liquid propellant tanks. The liquid slosh dynamics are included by using an improved moving pulsating ball model. The moving pulsating ball model is an equivalent mechanical model that is capable of imitating the liquid reorientation process, especially for large-amplitude slosh. This model is improved by incorporating a static capillary force and an effective mass factor. The improvements are validated with previously published experiment results. The spacecraft attitude maneuver is implemented by the momentum transfer technique. The designed feedback control strategy is demonstrated to be efficient and robust for the coupled liquid-filled spacecraft system. For the two-tank system, two eccentric cases of concern are an asymmetric tank arrangement and an unbalanced propellant mass distribution in the two tanks. The effects of the two eccentric cases on sloshing torque and control torque are investigated. Some conclusions obtained are useful in the overall design of liquid-filled spacecraft.
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Acknowledgments
The authors sincerely acknowledge the financial support of the National Natural Science Foundation of China (NNSFC) (Grant Nos.11472041 and 11532002) and the Research Fund for the Doctoral Program of Higher Education of China through Grant No. 20131101110002. The authors are also very grateful to J. P. B. Vreeburg for his invaluable help with offering references and suggestions for this paper.
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Information & Authors
Information
Published In
Journal of Aerospace Engineering
Volume 29 • Issue 6 • November 2016
Copyright
© 2016 American Society of Civil Engineers.
History
Received: Dec 14, 2015
Accepted: Mar 10, 2016
Published online: Jun 6, 2016
Published in print: Nov 1, 2016
Discussion open until: Nov 6, 2016
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