Most of earth observation satellites have a single solar array due to the requirement imposed by the optical sensor visibility. This requirement makes spacecraft configuration highly unsymmetric, which produces particular dynamic characteristics. When the actuator such as gas-jet thrusters is used for translational orbit control, transitional imbalance torque is caused even if the sum of translational force vectors pass through the center of mass. In this paper, this particular dynamics for unsymmetric flexible spacecrafts is formulated and the method to reduce the transitional imbalance is proposed.
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