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18 October 1996 Understanding GOES-8 dynamics
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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.
© (1996) COPYRIGHT Society of Photo-Optical Instrumentation Engineers (SPIE). Downloading of the abstract is permitted for personal use only.
Sivakumar Tadikonda and Sandra Cauffman "Understanding GOES-8 dynamics", Proc. SPIE 2812, GOES-8 and Beyond, (18 October 1996); https://doi.org/10.1117/12.254115
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