| 小倾角GSO卫星的转移轨道优化设计 |
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| 引用本文： | 李向阳,经姚翔,赵宏.小倾角GSO卫星的转移轨道优化设计[J].航天器工程,2014,23(5):18-22. |
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| 作者姓名： | 李向阳 经姚翔 赵宏 |
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| 作者单位： | 中国空间技术研究院通信卫星事业部,北京,100094 |
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| 摘 要： | 分析了采用小倾角地球同步轨道(GSO)策略后轨道转移变轨推进剂消耗增加的原因,对传统的地球同步转移轨道(GTO)提出了优化措施,根据月份发射的不同,选取不同的转移轨道近地点幅角ω,降低了转移轨道变轨所需的速度增量。速度增量平均降幅可达到55m/s,相当于延长了该卫星1年的推进剂消耗寿命。文章的研究结果可为优化卫星总体设计提供参考。
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| 关 键 词： | 小倾角 地球同步轨道 位置保持 升交点赤经 |
Optimized Transfer Orbit Design of Low-inclination GSO Satellite |
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| LI Xiangyang,JING Yaoxiang,ZHAO Hong.Optimized Transfer Orbit Design of Low-inclination GSO Satellite[J].Spacecraft Engineering,2014,23(5):18-22. |
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| Authors: | LI Xiangyang JING Yaoxiang ZHAO Hong |
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| Institution: | 1.Institute of Telecommunication Satellite, China Academy of Space Technology, Beijing 100094, China) |
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| Abstract: | The causes of the propellant consumption increases in transfer-orbit maneuver are analyzed,and the optimized method of GTO is employed to decrease the velocity increment,in which the argument of perigee is optimized.The velocity increment of orbit transfer to its final location for GEO satellites decreases by about 55m/s with the optimization of GTO,which will prolongs the life of satellites for one more year.The research results can provide a reference to optimization of satellite system design. |
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| Keywords: | low-inclination GSO station keeping right ascension of ascending node(RAAN) |
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