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Thermally induced spin rate ripple on spacecraft with long radial appendagesA thermally induced spin rate ripple hypothesis is proposed to explain the spin rate anomaly observed on ISEE-B. It involves the two radial 14.5 meter beryllium copper tape ribbons going in and out of the spacecraft hub shadow. A thermal lag time constant is applied to the thermally induced ribbon displacements which perturb the spin rate. It is inferred that the averaged thermally induced ribbon displacements are coupled to the ribbon angular motion. A possible exponential build up of the inplane motion of the ribbon which in turn causes the spin rate ripple, ultimately limited by damping in the ribbon and spacecraft is shown. It is indicated that qualitative increase in the oscillation period and the thermal lag is fundamental for the period increase. found that numerical parameter values required to agree with in orbit initial exponential build up are reasonable; those required for the ripple period are somewhat extreme.
Document ID
19840008181
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Fedor, J. V. (NASA Goddard Space Flight Center Greenbelt, MD, United States)
Date Acquired
September 4, 2013
Publication Date
August 1, 1983
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
NASA-TM-85058
NAS 1.15:85058
Accession Number
84N16249
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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