Hybrid spacecraft attitude control system

Authors

  • R Varatharajoo
  • R Ajir
  • T Ahmad

DOI:

https://doi.org/10.1260/175095407781421586

Abstract

The hybrid subsystem design could be an attractive approach for futurespacecraft to cope with their demands. The idea of combining theconventional Attitude Control System and the Electrical Power System ispresented in this article. The Combined Energy and Attitude ControlSystem (CEACS) consisting of a double counter rotating flywheel assemblyis investigated for small satellites in this article. Another hybrid systemincorporating the conventional Attitude Control System into the ThermalControl System forming the Combined Attitude and Thermal ControlSystem (CATCS) consisting of a "fluid wheel" and permanent magnets isalso investigated for small satellites herein. The governing equationsdescribing both these novel hybrid subsystems are presented and theironboard architectures are numerically tested. Both the investigated novelhybrid spacecraft subsystems comply with the reference missionrequirements.The hybrid subsystem design could be an attractive approach for futurespacecraft to cope with their demands. The idea of combining theconventional Attitude Control System and the Electrical Power System ispresented in this article. The Combined Energy and Attitude ControlSystem (CEACS) consisting of a double counter rotating flywheel assemblyis investigated for small satellites in this article. Another hybrid systemincorporating the conventional Attitude Control System into the ThermalControl System forming the Combined Attitude and Thermal ControlSystem (CATCS) consisting of a "fluid wheel" and permanent magnets isalso investigated for small satellites herein. The governing equationsdescribing both these novel hybrid subsystems are presented and theironboard architectures are numerically tested. Both the investigated novelhybrid spacecraft subsystems comply with the reference missionrequirements.

References

Barde, H., Energy Storage Wheel Feasibility Study, Proceedings of 4th Tribology Forum and Advances in Space Mechanisms, No. 10, European Space Agency, Noordwijk, The Netherlands, 2001, 1-26.

Guyot, P., Barde, H. and Griseri, G.. Flywheel Power and Attitude Control System (FPACS), Proceedings of 4th ESA Conference on Spacecraft Guidance, Navigation and Control System, No. ESA-SP-425, European Space Agency, Noordwijk, The Netherlands, 1999, 371-378.

Renuganth, V. and Fasoulas, S., Methodology for the Development of Combined Energy and Attitude Control Systems for Satellites, Aerospace Science & Technology, 2002, 6, 303-311. https://doi.org/10.1016/s1270-9638(02)01157-4

Renuganth, V., Kahle, R. and Fasoulas, S., Approach for Combining Attitude and Thermal Control Systems, Journal of Spacecraft and Rockets, 2003, 40, 657-664. https://doi.org/10.2514/2.6914

Renuganth, V. and Tarmizi, M., Flywheel Energy Storage for Spacecraft, Journal of Aircraft Engineering and Aerospace Aerospace Technology, 2004, 76, 384-390. https://doi.org/10.1108/00022660410545492

Renuganth, V. and Kahle, R., A Review of Spacecraft Conventional and Synergistic Systems, Journal of Aircraft Engineering and Aerospace Technology, 2005, 77, 131-141.

Published

2007-06-30

How to Cite

Varatharajoo, R., Ajir, R. and Ahmad, T. (2007) “Hybrid spacecraft attitude control system”, The International Journal of Multiphysics, 1(2), pp. 221-230. doi: 10.1260/175095407781421586.

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