Statistics – Applications
Scientific paper
Nov 1976
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1976cemec..14..307e&link_type=abstract
(Conference on Mathematical Methods in Celestial Mechanics, 5th, Oberwolfach, West Germany, Aug. 24-30, 1975.) Celestial Mechani
Statistics
Applications
Orbital Maneuvers, Satellite Attitude Control, Satellite Perturbation, Spacecraft Maneuvers, Spin Stabilization, Differential Equations, Euler Equations Of Motion, Fourier Series, Inertial Coordinates, Long Term Effects, Nutation, Optimization
Scientific paper
The differential equations governing the attitude motion of a spin-stabilized satellite are solved analytically by applying Kevorkian's (1966) two-variable expansion procedure, where the single independent variable is replaced by two such variables. Two sets of partial differential equations and solutions, in the zero and first orders of the small parameter epsilon, are obtained by substituting the two-variable asymptotic expansions in the governing equations. The long-term equations obtained are integrated, mean acceleration and velocity increments are derived, and an approximate semianalytical solution is determined. Applications of this solution to maneuver prediction, maneuver parameter correction, and maneuver parameter optimization are demonstrated with numerical examples.
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