PLASMA PROPULSION FOR GEOSTATIONARY SATELLITES AND INTERPLANETARY SPACECRAFT
PLASMA PROPULSION FOR GEOSTATIONARY SATELLITES AND INTERPLANETARY SPACECRAFT
复制标题
对地静止卫星和行星际飞船的等离子体推进
DOI：
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发表时间：
2011
期刊：
影响因子：
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通讯作者：
S. Zurbach
中科院分区：
文献类型：
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作者：
M. Dudeck;F. Doveil;N. Arcis;S. Zurbach
地球静止通信卫星从与发射装置第三级分离到脱离轨道运行都需要推进系统。在与第三级分离时，卫星被注入到远地点距离地球表面36000公里的转移轨道上。在该轨道的远地点，施加1-3牛顿的推力，速度增加约1.9米/秒，将卫星移至准圆形和准赤道轨道。还需要一个或两个月的时间来使轨道呈圆形和赤道，打开太阳能电池板，核实仪器，修改卫星姿态，并将卫星置于其工作经度。卫星在整个使命期间（15至20年）必须保持在这一工作位置。然而，卫星根据月球和太阳的轨道，地球的不均匀性和太阳辐射压力移动。在地球静止轨道的高度上，阻力效应可以忽略不计。主要的影响是月日相互作用，它大于地球的不均匀性和太阳辐射的影响。因此，需要推进器
Geostationary telecommunication satellites require propulsion systems from its separation from the third stage of the launcher to the de-orbiting operation. At this separation with the third stage, the satellite is injected on a transfer orbit with an apogee at 36000 km from Earth surface. At the apogee of this orbit an applied thrust of 1-3 N gives an increment of velocity of ~1,9 m/s and moves the satellite to a quasi-circular and quasi-equatorial orbit. One or two supplementary months are necessary to make the orbit circular and equatorial, to open solar panels, to verify the instruments, to modify the satellite attitude and to set the satellite at its working longitude. The satellite has to be maintained at this working position throughout the mission (15 to 20 years). However the satellite moves in accordance with Lunar and Sun trajectories, inhomogeneity of the Earth and radiative Sun pressure. At the altitude of the geostationary orbit (GEO) the drag effect is negligible. The predominant effect is the Lunar-Solar interactions which are greater than the Earth inhomogeneity and the Sun radiation effects. Consequently, thrusters are required