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The investigation of tethered satellite system dynamicsThe analysis of the rotational dynamics of the satellite was focused on the rotational amplitude increase of the satellite, with respect to the tether, during retrieval. The dependence of the rotational amplitude upon the tether tension variation to the power 1/4 was thoroughly investigated. The damping of rotational oscillations achievable by reel control was also quantified while an alternative solution that makes use of a lever arm attached with a universal joint to the satellite was proposed. Comparison simulations between the Smithsonian Astrophysical Observatory and the Martin Marietta (MMA) computer code of reteival maneuvers were also carried out. The agreement between the two, completely independent, codes was extremely close, demonstrating the reliability of the models. The slack tether dynamics during reel jams was analytically investigated in order to identify the limits of applicability of the SLACK3 computer code to this particular case. Test runs with SLACK3 were also carried out.
Document ID
19860022159
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Lorenzini, E. C. (Smithsonian Astrophysical Observatory Cambridge, MA, United States)
Date Acquired
September 5, 2013
Publication Date
June 1, 1986
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
QR-7
NASA-CR-178895
NAS 1.26:178895
Accession Number
86N31631
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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