| 摘要 |
PURPOSE: To minimize the influence of the thruster plume on experimental devices installed outside and to reduce propellant consumption, by firing thrusters separately and selectively when the thrust axes are almost parallel to a maneuver direction while a spacecraft is rotating about its spin axis. CONSTITUTION: First thrusters 301 , 302 and a pair of second thrusters 30 are installed at the periphery of a spacecraft, and each of thrust axes 401 , 402 is shifted relative to its radial direction by an offset angleα. The thrusters 301 , 302 are fired selectively and alternately when the thrust axes 401 , 402 are generally parallel to a vector D while a spacecraft is rotating to correct its orbital velocity. Therefore, the thruster 301 is fired when a transverse axis 60 is shifted by the angleαto a maneuver direction along the orbital velocity vector. and the thruster 302 is fired when a common support member of a pair of the thrusters 301 , 302 rotates around a spin axis 20 by the angle of 2α.
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