TRAJECTORY DESIGN FOR THE LUNAR POLAR HYDROGEN MAPPER MISSION

被引：0

作者：

Genova, Anthony L. ^{[1
,2
]}

Dunham, David W. ^{[3
]}

机构：

[1] NASA, Ames Res Ctr, Mission Design Div, Moffett Field, CA 94035 USA

[2] Florida Inst Technol, Mech & Aerosp Engn Dept, Melbourne, FL 32901 USA

[3] KinetX Inc, 7913 Kara Court, Greenbelt, MD 20770 USA

来源：

SPACEFLIGHT MECHANICS 2017, PTS I - IV | 2017年 / 160卷

关键词：

D O I：

暂无

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The presented trajectory was designed for the Lunar Polar Hydrogen Mapper (LunaH-Map) 6U CubeSat, which was awarded a ride on NASA's Space Launch System (SLS) with Exploration Mission 1 (EM-1) via NASA's 2015 SIMPLEX proposal call. After deployment from EM-1's upper stage (which is planned to enter heliocentric space via a lunar flyby), the LunaH-Map CubeSat will alter its trajectory via its low-thrust ion engine to target a lunar flyby that yields a Sun-Earth-Moon weak stability boundary transfer to set up a ballistic lunar capture. Finally, the orbit energy is lowered to reach the required quasi-frozen science orbit with periselene above the lunar south pole.

引用

页码：3219 / 3233

页数：15

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