AIAA Journal · 1963 · 20 citations · 1 references
Natural SciencesAerospace EngineeringMathematicsCelestial MechanicsDifferential EquationsDynamical SystemsAttitude ControlOrbital DynamicsOrbital StabilitySatellite Orbit DynamicsSatellite OrbitsStability TheoryCircular OrbitsFloquet DynamicsFloquet StabilityFloquet TheoryRotational SymmetrySatellite DynamicsSatellite Orbital DynamicsStability Conditions
This investigation deals with motion, in a circular orbit, of a satellite consisting of a rigid body which possesses an axis of rotational symmetry and carries, on this axis, two particles that perform prescribed oscillations while the axis remains nearly normal to the plane of the orbit. Differential equations governing attitude angles are derived, stability conditions are obtained by using Floquet theory to study the boundedness of the solutions of these equations., and the practical feasibility of this method of stabilization is examined by reference to a numerical example.
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