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Deployment Mechanisms on the Fast Satellite: Magnetometer, Radial Wire, and Axial Booms

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Abstract

The Fast Auroral SnapshoT (FAST) satellite was launched by a Pegasus XL on August 21, 1996. This was the second launch in the NASA SMall EXplorer (SMEX) program. Early in the mission planning the decision was made to have the University of California at Berkeley Space Sciences Laboratory (UCB-SSL) mechanical engineering staff provide all of the spacecraft appendages, in order to meet the short development schedule, and to insure compatibility. This paper describes the design development, testing and on-orbit deployment of these boom systems: the 2 m carbon fiber magnetometer booms, the 58 m tip to tip spin-plane wire booms, and the 7 m dipole axial stiff booms.

Keywords

Spin Axis Attitude Control System Trap Door Deployment Mechanism Instrument Data Processing Unit 
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References

  1. Lai, S. T. and Bhavnani, K. H.: Dynamics of Satellite Wire Boom Systems, AFCRL-TR-75-0220.Google Scholar
  2. Meirovitch, L. and Calico, R. E.: 1972, The Stability of Motion of Satellites with Flexible Appendages, NASA CR-1978.Google Scholar
  3. Staugaitis, C. L. and Predmore, R. E.: 1973, Thermal Static Bending of Deploy able Interlocked Booms, NASA TN D-7243.Google Scholar
  4. Thomson, W. T.: 1961, Introduction to Space Dynamics, J. Wiley, New York.Google Scholar

Copyright information

© Springer Science+Business Media Dordrecht 2001

Authors and Affiliations

  1. 1.Samuel Silver Space Sciences LaboratoryUniversity of California at BerkeleyUSA
  2. 2.Besuner Consulting ServicesMaderaUSA
  3. 3.Lockheed Martin Space Mission Systems & ServicesHoustonUSA

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