Spacecraft detumbling through energy dissipationThe attitude motion of a tumbling, rigid, axisymmetric spacecraft is considered. A methodology for detumbling the spacecraft through energy dissipation is presented. The differential equations governing this motion are stiff, and therefore an approximate solution, based on the variation of constants method, is developed and utilized in the analysis of the detumbling strategy. Stability of the detumbling process is also addressed.
Document ID
19930015507
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Fitz-Coy, Norman (Florida Univ. Gainesville, FL, United States)
Chatterjee, Anindya (Florida Univ. Gainesville, FL, United States)
Date Acquired
September 6, 2013
Publication Date
February 1, 1993
Publication Information
Publication: NASA. Goddard Space Flight Center, Flight Mechanics(Estimation Theory Symposium, 1992