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Integration of Low G Sloshing Models with Spacecraft Attitude Control Simulators by Damien Theureau; Jean Mignot; Sebastien Tanguy is a scholarly article available to read on EtoBox.

What is Integration of Low G Sloshing Models with Spacecraft Attitude Control Simulators about?

Very High Resolution Science and Observation missions are more and more demanding both in terms of high stability and in terms of maneuverability. But those two requirements are not compatible; indeed the rotation of the spacecraft induces sloshing of the propellant inside the tanks. And such fluid movement induces perturbation back on the platform. Given the high level of pointing stability that must be achieved such perturbation can be a major driver in the system trade-off.In this context, sloshing model development has been initiated under CNES contract. It is being conducted by Astrium Satellites as prime contractor with the support of IMFT laboratory. The objectives were first to develop a representative analytical model of liquid sloshing under low acceleration condition then to integrate it within a complete attitude control system and finally to assess the slosh impact on a reference mission in terms of actuators sizing and pointing performances.The paper presents the approach taken during this study, the definition and integration of the analytical sloshing model and proposes a method that can be followed when treating sloshing issues.

Author

Damien Theureau; Jean Mignot; Sebastien Tanguy

Publisher

American Institute of Aeronautics and Astronautics

Published

2013

Language

EN