| 摘要 |
PURPOSE: A method is provided to ensure stability of an artificial satellite system by eliminating a thermal flutter phenomenon of a solar array caused when the artificial satellite passes through an eclipse. CONSTITUTION: A method comprises a first step of allowing a control unit to calculate an angle formed by an artificial satellite and the sun using a solar energy measure data, a second step of judging whether the body of the artificial satellite initially enters an eclipse area using the angle calculated in the first step, a third step of allowing the control unit to return to the first step if it is judged that the body of the satellite is not entered in the second step, and allowing the control unit to rotate the solar array by 90 degree so that an angle between the sun and the solar array surface becomes horizontal if it is judged that the body of the satellite initially entered, a fourth step of allowing the control unit to calculate an angle between the satellite and sun using a solar energy measure data, a fifth step of judging whether the body of the satellite is completely escaped from the eclipse area, and a sixth step of allowing the control unit to return to the fourth step if it is judged that the body of the satellite is not completely escaped from the eclipse area, and allowing the control unit to rotate the solar array by 90 degree so that an angle between the sun and the solar array surface becomes vertical.
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