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 RCS thruster is used, sensitivity from the displacement force to the attitude varies depending on the control frequency. This causes the imbalance between negative torque and positive torque on the main body, in other words, rotational center shifts from the mass center of the spacecraft. In this paper, this unsymmetric characteristic is formulated, and even more bending moment and shearing force acting on the root of the solar array are formulated. And then notations for designing a structure and a controller are indicated. Given a numerical model, formulated characteristics are also shown quantitatively.
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