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Proceedings Paper

Understanding GOES-8 dynamics
Author(s): Sivakumar Tadikonda; Sandra Cauffman
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Paper Abstract

The dynamics of GOES-8 is simulated using an articulated, flexible, multi-body dynamics model. The solar array on this spacecraft is flexible, and is articulated with a stepper motor. Three stepping configurations are available: 1 0.007 degree single step every 1.69 seconds, and two double stepping options that were provided in order to deadbeat the solar array oscillations. In this paper, models that are commonly employed for simulating the dynamics of spacecraft with flexible appendages are reviewed and the advantages of the present model over other methods are emphasized. Simulation results show good agreement with the flight data when orbital environmental effects are accounted for. This study has significant implications for both the design and dynamic modeling of articulating, flexible solar arrays attached to the spacecraft, especially when payloads such as the Solar X-ray Imager with tight pointing requirements are to ge located on the solar array. The implications are i) appropriate dynamic models must be employed, ii) the solar array actuating device must be such that vibrational modes of the array are not excited, and iii) conservative damping estimates must be used when empirical values are not available.

Paper Details

Date Published: 18 October 1996
PDF: 12 pages
Proc. SPIE 2812, GOES-8 and Beyond, (18 October 1996); doi: 10.1117/12.254115
Show Author Affiliations
Sivakumar Tadikonda, McDonnell Douglas Aerospace (United States)
Sandra Cauffman, NASA Goddard Space Flight Ctr. (United States)

Published in SPIE Proceedings Vol. 2812:
GOES-8 and Beyond
Edward R. Washwell, Editor(s)

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