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Attitude Dynamics and Control of Liquid Filled Spacecraft with Large Amplitude Fuel Slosh

Published online by Cambridge University Press:  15 July 2016

M.-L. Deng  and
B.-Z. Yue
M.-L. Deng
Affiliation:
Department of Mechanics School of Aerospace Engineering Beijing Institute of Technology Beijing, China
B.-Z. Yue*
Affiliation:
Department of Mechanics School of Aerospace Engineering Beijing Institute of Technology Beijing, China
*
*Corresponding author (bzyue@bit.edu.cn)
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Abstract

This paper focuses on the attitude dynamics and control of liquid filled spacecraft, and the large amplitude fuel slosh dynamics is 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 whole liquid reorientation process, specifically for the occurrence of large amplitude slosh. This model is improved by incorporating a static capillary force and an effective mass factor. The improvements on this model are validated with previously published experiment results. The spacecraft attitude maneuver is implemented by the momentum transfer technique, and the feedback control strategy is designed based on Lyapunov theory. The effects of liquid viscosity, tank location and desired steady time on sloshing torque and control torque are investigated. The attitude control strategy applied in this paper is proved to be applicable for the coupled liquid filled spacecraft system. The obtained conclusions are useful to aid in liquid filled spacecraft overall design.

Keywords

Liquid filled spacecraftAttitude maneuverLarge amplitude liquid sloshThe moving pulsating ball model

Information

Type
Research Article
Information
Journal of Mechanics , Volume 33 , Issue 1 , February 2017 , pp. 125 - 136
Copyright
Copyright © The Society of Theoretical and Applied Mechanics 2017 

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