Dynamics of satellite subject to gravitational and aerodynamic torques. Investigation of equilibria
Dynamics of attitude motion of a satellite moving along a circular orbit under influence of gravitational and aerodynamic torque is investigated. A symbolic-numerical method for determining all equilibrium orientations of the satellite in the orbital coordinate system with given aerodynamic torque and given principal central moments of inertia is proposed. Conditions of equilibria existence are obtained depending on four dimensionless parameters of the system. All bifurcational values of parameters at which there is a change of numbers of equilibrium orientations are determined. Evolution of domains in the space of parameters which correspond to various numbers of equilibria are carried out in detail. Relationship with axisymmetrical cases of satellite is considered. It is shown that the number of equilibria of the satellite in general case not be less than 8 and not more than 24.