Trajectory design for a cislunar CubeSat leveraging dynamical systems techniques: The Lunar IceCube mission

被引：36

作者：

Bosanac, Natasha ^{[1
,3
]}

Cox, Andrew D. ^{[1
]}

Howell, Kathleen C. ^{[1
]}

Folta, David C. ^{[2
]}

机构：

[1] Purdue Univ, Dept Aeronaut & Astronaut, W Lafayette, IN 47906 USA

[2] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA

[3] Univ Colorado, Colorado Ctr Astrodynam Res, Smead Dept Aerosp Engn Sci, Boulder, CO 80309 USA

来源：

ACTA ASTRONAUTICA | 2018年 / 144卷

关键词：

Trajectory design; CubeSats; Small satellites; Multi-body dynamics; Dynamical systems theory; MOON;

D O I：

10.1016/j.actaastro.2017.12.025

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Lunar IceCube is a 6U CubeSat that is designed to detect and observe lunar volatiles from a highly inclined orbit. This spacecraft, equipped with a low-thrust engine, is expected to be deployed from the upcoming Exploration Mission-1 vehicle. However, significant uncertainty in the deployment conditions for secondary payloads impacts both the availability and geometry of transfers that deliver the spacecraft to the lunar vicinity. A framework that leverages dynamical systems techniques is applied to a recently updated set of deployment conditions and spacecraft parameter values for the Lunar IceCube mission, demonstrating the capability for rapid trajectory design.

引用

页码：283 / 296

页数：14

共 48 条

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