Design and analysis of an extended mission of CE-2: From lunar orbit to Sun-Earth L2 region

Dong Qiao; Pingyuan Cui; Yamin Wang; Jiangchuan Huang; Linzhi Meng; Degang Jie

doi:10.1016/j.asr.2013.11.032

Design and analysis of an extended mission of CE-2: From lunar orbit to Sun-Earth L2 region

Dong Qiao^*, Pingyuan Cui, Yamin Wang, Jiangchuan Huang, Linzhi Meng, Degang Jie

^*Corresponding author for this work

School of Aerospace Engineering

Research output: Contribution to journal › Article › peer-review

7 Citations (Scopus)

Abstract

Chang'E-2 (CE-2) has firstly successfully achieved the exploring mission from lunar orbit to Sun-Earth L2 region. In this paper, we discuss the design problem of transfer trajectory and at the same time analyze the visible segment of Tracking, Telemetry & Control (TT&C) system for this mission. Firstly, the four-body problem of Sun-Earth-Moon and Spacecraft can be decoupled in two different three-body problems (Sun-Earth + Moon Restricted Three-Body Problems (RTBPs) and Earth-Moon ephemeris model). Then, the transfer trajectory segments in different model are computed, respectively, and patched by Poincaré sections. The full-flight trajectory including transfer trajectory from lunar orbit to Sun-Earth L2 region and target Lissajous orbit is obtained by the differential correction method. Finally, the visibility of TT&C system at the key time is analyzed. Actual execution of CE-2 extended mission shows that the trajectory design of CE-2 mission is feasible.

Original language	English
Pages (from-to)	2087-2093
Number of pages	7
Journal	Advances in Space Research
Volume	54
Issue number	10
DOIs	https://doi.org/10.1016/j.asr.2013.11.032
Publication status	Published - 15 Nov 2014

Keywords

Analysis of tracking and control
ChangE-2
Four-body problem
Lissajous orbit
Transfer trajectory

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title = "Design and analysis of an extended mission of CE-2: From lunar orbit to Sun-Earth L2 region",

abstract = "Chang'E-2 (CE-2) has firstly successfully achieved the exploring mission from lunar orbit to Sun-Earth L2 region. In this paper, we discuss the design problem of transfer trajectory and at the same time analyze the visible segment of Tracking, Telemetry & Control (TT&C) system for this mission. Firstly, the four-body problem of Sun-Earth-Moon and Spacecraft can be decoupled in two different three-body problems (Sun-Earth + Moon Restricted Three-Body Problems (RTBPs) and Earth-Moon ephemeris model). Then, the transfer trajectory segments in different model are computed, respectively, and patched by Poincar{\'e} sections. The full-flight trajectory including transfer trajectory from lunar orbit to Sun-Earth L2 region and target Lissajous orbit is obtained by the differential correction method. Finally, the visibility of TT&C system at the key time is analyzed. Actual execution of CE-2 extended mission shows that the trajectory design of CE-2 mission is feasible.",

keywords = "Analysis of tracking and control, ChangE-2, Four-body problem, Lissajous orbit, Transfer trajectory",

author = "Dong Qiao and Pingyuan Cui and Yamin Wang and Jiangchuan Huang and Linzhi Meng and Degang Jie",

year = "2014",

month = nov,

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doi = "10.1016/j.asr.2013.11.032",

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T1 - Design and analysis of an extended mission of CE-2

T2 - From lunar orbit to Sun-Earth L2 region

AU - Qiao, Dong

AU - Cui, Pingyuan

AU - Wang, Yamin

AU - Huang, Jiangchuan

AU - Meng, Linzhi

AU - Jie, Degang

PY - 2014/11/15

Y1 - 2014/11/15

N2 - Chang'E-2 (CE-2) has firstly successfully achieved the exploring mission from lunar orbit to Sun-Earth L2 region. In this paper, we discuss the design problem of transfer trajectory and at the same time analyze the visible segment of Tracking, Telemetry & Control (TT&C) system for this mission. Firstly, the four-body problem of Sun-Earth-Moon and Spacecraft can be decoupled in two different three-body problems (Sun-Earth + Moon Restricted Three-Body Problems (RTBPs) and Earth-Moon ephemeris model). Then, the transfer trajectory segments in different model are computed, respectively, and patched by Poincaré sections. The full-flight trajectory including transfer trajectory from lunar orbit to Sun-Earth L2 region and target Lissajous orbit is obtained by the differential correction method. Finally, the visibility of TT&C system at the key time is analyzed. Actual execution of CE-2 extended mission shows that the trajectory design of CE-2 mission is feasible.

AB - Chang'E-2 (CE-2) has firstly successfully achieved the exploring mission from lunar orbit to Sun-Earth L2 region. In this paper, we discuss the design problem of transfer trajectory and at the same time analyze the visible segment of Tracking, Telemetry & Control (TT&C) system for this mission. Firstly, the four-body problem of Sun-Earth-Moon and Spacecraft can be decoupled in two different three-body problems (Sun-Earth + Moon Restricted Three-Body Problems (RTBPs) and Earth-Moon ephemeris model). Then, the transfer trajectory segments in different model are computed, respectively, and patched by Poincaré sections. The full-flight trajectory including transfer trajectory from lunar orbit to Sun-Earth L2 region and target Lissajous orbit is obtained by the differential correction method. Finally, the visibility of TT&C system at the key time is analyzed. Actual execution of CE-2 extended mission shows that the trajectory design of CE-2 mission is feasible.

KW - Analysis of tracking and control

KW - ChangE-2

KW - Four-body problem

KW - Lissajous orbit

KW - Transfer trajectory

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SP - 2087

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JO - Advances in Space Research

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ER -

Design and analysis of an extended mission of CE-2: From lunar orbit to Sun-Earth L2 region

Abstract

Keywords

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