Trajectories and Orbital Maneuvers for the First Libration-Point Satellite
Trajectories and Orbital Maneuvers for the First Libration-Point Satellite
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DOI：
10.2514/3.56034
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发表时间：
1980-11
影响因子：
2.6
通讯作者：
R. Farquhar;D. Muhonen;C. R. Newman;Howard S . Heubergerg
中科院分区：
文献类型：
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作者：
R. Farquhar;D. Muhonen;C. R. Newman;Howard S . Heubergerg
1978年8月12日，国际日地探测器3号（ISEE-3）向日地平动点LI发射。1978年11月20日，该航天器被放置到围绕LI点的“光环轨道”，从而成为第一颗天秤座卫星。在其100天的转移轨道期间，ISEE-3徘徊在太阳和地球引力效应相当的区域，导致了一些关于光环轨道插入机动策略的有趣权衡。进入轨道后，需要进行位置保持机动，以保持晕圈轨道的微妙平衡。详细介绍了1979年5月14日完成第一个晕圈轨道之前执行的所有AV机动。还讨论了轨道选择、轨道设计和ISEE-3使命的科学目标。
On August 12,1978, a scientific spacecraft called International Sun-Earth Explorer-3 (ISEE-3) was launched towards the interior sun-Earth libration point, LI. The spacecraft was placed into a "halo orbit" around the LI point on November 20, 1978, thus becoming the first libration-point satellite. During its 100-day transfer trajectory, ISEE-3 lingered in a region where the gravitational effects of the sun and the Earth are comparable, leading to some interesting tradeoffs concerning the maneuver strategy for halo-orbit insertion. Following orbit insertion, stationkeeping maneuvers were required to maintain the delicate equilibrium in the halo orbit. Details are presented for all of the A V maneuvers that were executed prior to the completion of the first halo orbit on May 14, 1979. Orbit selection, trajectory design, and the scientific objectives of the ISEE-3 mission are also discussed.