Abstract
The mutual interaction of orbit-attitude maneuvers of spin-stablized satellites is investigated by application of theTwo Variable Expansion Procedure to the Euler equations. The resulting semi-analytical solution describes the short periodic nutation, the long-term attitude variation and the mean linear acceleration of the center of mass. Some applications of the solution are shown by means of a few examples.
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References
Eckstein, M. C.: 1974, European Space Research Organization (ESRO), ESOC-Contract 603/74/T, Final Report, pp. 35–38.
Eckstein, M. C.: 1975, Deutsche Forschungs- und Versuchsanstalt für Luft- und Raumfahrt (DFVLR), Interner Bericht Nr. 552-75/9, pp. 18–23.
Kevorkian, J.: 1966, ‘The Two Variable Expansion Procedure for the Approximate Solution of Certain Nonlinear Differential Equations’, Lectures inAppl. Math. 7;Space Mathematics, Part III;Amer. Math. Soc., J. B. Rosser (ed.), Providence, R.I., USA.
Magnus, K.: 1971,Kreisel, Springer-Verlag, Berlin, Heidelberg, New York, p. 64ff.
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Eckstein, M.C. An approximate semi-analytical solution for orbit- and attitude maneuvers of spin-stabilized satellites. Celestial Mechanics 14, 307–320 (1976). https://doi.org/10.1007/BF01228515
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DOI: https://doi.org/10.1007/BF01228515