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Advisor(s)
Abstract(s)
We study the dynamics of the rotational motion of a gyrostat satellite moving in the central Newtonian force field along a circular orbit. We propose a method for determining the equilibrium attitudes (equilibrium orientations) of a gyrostat satellite in the orbital coordinate system for given values of the gyrostatic moment vector and principal central moments of inertia, and obtain their existence conditions. For each equilibrium orientation, sufficient conditions for stability are obtained using a generalized energy integral such as a Lyapunov function. We conduct a detailed numerical analysis of domains where the stability conditions for equilibrium attitudes are satisfied depending on four dimensionless parameters of the problem. It is shown that the number of equilibrium attitudes of a gyrostat satellite for which the sufficient conditions of stability are satisfied in the general case varies from four to two with an increase in the magnitude of a gyrostatic moment. The results obtained in this paper can be used for constructing gravitational systems of control over the orientation of the Earth’s artificial satellites.
Description
Keywords
Positions Vector Real Root System Science International Direction Cosine Stable Orientation Axisymmetric Case Lyapunov functions Satellites Stability Dimensionless Parameters Equilibrium Orientations Existence Conditions Gravitational Systems Gyrostat Satellite Orbital Coordinate System Rotational Motion Stability Condition Orbits
Citation
S. A. Gutnik, L. Santos, V. A. Sarychev, A. Silva. “Dynamics of gyrostat satellite subject to gravitational torque. Investigation of stability equilibria”, Journal of Computer and Systems Sciences International, Vol. 54, No.3, pp 469-482, 2015, DOI: 10.1134/S1064230715030107
Publisher
MAIK Nauka/Interperiodica