| 摘要 |
PROBLEM TO BE SOLVED: To maximize payload weight and mission longevity by using an electric propulsive thruster of a satellite only for simultaneous correction of increase of orbital inclination and orbital eccentricity and using a chemical propulsive thruster for the purpose of correcting an orbital length radius. SOLUTION: A satellite 20 having chemical propulsive and electric propulsive thrusters 26, 27 is launched on a stationary orbit travelling around a central body. The electric propulsive thruster 27 is ignited and corrects meridional libration and zonal libration caused by increase of orbital inclination and orbital eccentricity of the satellite. Additionally, the chemical propulsive thruster 26 is ignited and corrects zonal libration caused by increase of an orbital length radius. Furthermore it is possible to selectively point to the electric propulsive thruster 27 using gimbals, momentum damping is carried out and/or the chemical propulsive thruster 26 is additionally ignited, and in the case when the electric propulsive thruster 27 is ignited, a position of the satellite is maintained.
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