Optimal orbit control strategy design for low energy moon return

Liu Yue; Yingjing Qian; Ma Lin; Wuxing Jing

doi:10.1109/CCDC.2015.7162312

Optimal orbit control strategy design for low energy moon return

Liu Yue
, Yingjing Qian
, Ma Lin
, Wuxing Jing

School of Astronautics

DFH Satellite Co., Ltd.
Beijing University of Technology

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

2 Scopus citations

Abstract

The low energy moon return orbit has evident advantages in the fuel consumption but it's much sensitive to the initial states of the probe. To solve this problem, in this paper, the problem of accurate orbit control for low energy Moon return mission is studied. Firstly, based on the elliptical four body dynamical model, the dynamical characteristics of the low energy return orbit is analyzed. Then, the covariance analysis method is introduced to clarify the propagation properties of initial orbit errors. Finally, a three maneuvers orbit adjusting strategy is proposed according to the sensitiveness of the constraint against the accuracy of navigation and control impulse. By the simulation results, the strategy is able to guarantee an accurate height of reentry effectively.

Original language	English
Title of host publication	Proceedings of the 2015 27th Chinese Control and Decision Conference, CCDC 2015
Publisher	Institute of Electrical and Electronics Engineers Inc.
Pages	2342-2346
Number of pages	5
ISBN (Electronic)	9781479970179
DOIs	https://doi.org/10.1109/CCDC.2015.7162312
State	Published - 17 Jul 2015
Event	27th Chinese Control and Decision Conference, CCDC 2015 - Qingdao, China Duration: 23 May 2015 → 25 May 2015

Publication series

Name	Proceedings of the 2015 27th Chinese Control and Decision Conference, CCDC 2015

Conference

Conference	27th Chinese Control and Decision Conference, CCDC 2015
Country/Territory	China
City	Qingdao
Period	23/05/15 → 25/05/15

Keywords

Control Strategy
Covariance Analysis Method
Error Propagation
Low Energy
Moon Return Orbit

Access to Document

10.1109/CCDC.2015.7162312

Cite this

Yue, L., Qian, Y., Lin, M., & Jing, W. (2015). Optimal orbit control strategy design for low energy moon return. In Proceedings of the 2015 27th Chinese Control and Decision Conference, CCDC 2015 (pp. 2342-2346). Article 7162312 (Proceedings of the 2015 27th Chinese Control and Decision Conference, CCDC 2015). Institute of Electrical and Electronics Engineers Inc.. https://doi.org/10.1109/CCDC.2015.7162312

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title = "Optimal orbit control strategy design for low energy moon return",

abstract = "The low energy moon return orbit has evident advantages in the fuel consumption but it's much sensitive to the initial states of the probe. To solve this problem, in this paper, the problem of accurate orbit control for low energy Moon return mission is studied. Firstly, based on the elliptical four body dynamical model, the dynamical characteristics of the low energy return orbit is analyzed. Then, the covariance analysis method is introduced to clarify the propagation properties of initial orbit errors. Finally, a three maneuvers orbit adjusting strategy is proposed according to the sensitiveness of the constraint against the accuracy of navigation and control impulse. By the simulation results, the strategy is able to guarantee an accurate height of reentry effectively.",

keywords = "Control Strategy, Covariance Analysis Method, Error Propagation, Low Energy, Moon Return Orbit",

author = "Liu Yue and Yingjing Qian and Ma Lin and Wuxing Jing",

note = "Publisher Copyright: {\textcopyright} 2015 IEEE.; 27th Chinese Control and Decision Conference, CCDC 2015 ; Conference date: 23-05-2015 Through 25-05-2015",

year = "2015",

month = jul,

day = "17",

doi = "10.1109/CCDC.2015.7162312",

language = "英语",

series = "Proceedings of the 2015 27th Chinese Control and Decision Conference, CCDC 2015",

publisher = "Institute of Electrical and Electronics Engineers Inc.",

pages = "2342--2346",

booktitle = "Proceedings of the 2015 27th Chinese Control and Decision Conference, CCDC 2015",

address = "美国",

}

Yue, L, Qian, Y, Lin, M & Jing, W 2015, Optimal orbit control strategy design for low energy moon return. in Proceedings of the 2015 27th Chinese Control and Decision Conference, CCDC 2015., 7162312, Proceedings of the 2015 27th Chinese Control and Decision Conference, CCDC 2015, Institute of Electrical and Electronics Engineers Inc., pp. 2342-2346, 27th Chinese Control and Decision Conference, CCDC 2015, Qingdao, China, 23/05/15. https://doi.org/10.1109/CCDC.2015.7162312

Optimal orbit control strategy design for low energy moon return. / Yue, Liu; Qian, Yingjing; Lin, Ma et al.
Proceedings of the 2015 27th Chinese Control and Decision Conference, CCDC 2015. Institute of Electrical and Electronics Engineers Inc., 2015. p. 2342-2346 7162312 (Proceedings of the 2015 27th Chinese Control and Decision Conference, CCDC 2015).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

TY - GEN

T1 - Optimal orbit control strategy design for low energy moon return

AU - Yue, Liu

AU - Qian, Yingjing

AU - Lin, Ma

AU - Jing, Wuxing

PY - 2015/7/17

Y1 - 2015/7/17

N2 - The low energy moon return orbit has evident advantages in the fuel consumption but it's much sensitive to the initial states of the probe. To solve this problem, in this paper, the problem of accurate orbit control for low energy Moon return mission is studied. Firstly, based on the elliptical four body dynamical model, the dynamical characteristics of the low energy return orbit is analyzed. Then, the covariance analysis method is introduced to clarify the propagation properties of initial orbit errors. Finally, a three maneuvers orbit adjusting strategy is proposed according to the sensitiveness of the constraint against the accuracy of navigation and control impulse. By the simulation results, the strategy is able to guarantee an accurate height of reentry effectively.

AB - The low energy moon return orbit has evident advantages in the fuel consumption but it's much sensitive to the initial states of the probe. To solve this problem, in this paper, the problem of accurate orbit control for low energy Moon return mission is studied. Firstly, based on the elliptical four body dynamical model, the dynamical characteristics of the low energy return orbit is analyzed. Then, the covariance analysis method is introduced to clarify the propagation properties of initial orbit errors. Finally, a three maneuvers orbit adjusting strategy is proposed according to the sensitiveness of the constraint against the accuracy of navigation and control impulse. By the simulation results, the strategy is able to guarantee an accurate height of reentry effectively.

KW - Control Strategy

KW - Covariance Analysis Method

KW - Error Propagation

KW - Low Energy

KW - Moon Return Orbit

UR - https://www.scopus.com/pages/publications/84945558912

U2 - 10.1109/CCDC.2015.7162312

DO - 10.1109/CCDC.2015.7162312

M3 - 会议稿件

AN - SCOPUS:84945558912

T3 - Proceedings of the 2015 27th Chinese Control and Decision Conference, CCDC 2015

SP - 2342

EP - 2346

BT - Proceedings of the 2015 27th Chinese Control and Decision Conference, CCDC 2015

PB - Institute of Electrical and Electronics Engineers Inc.

T2 - 27th Chinese Control and Decision Conference, CCDC 2015

Y2 - 23 May 2015 through 25 May 2015

ER -

Yue L, Qian Y, Lin M, Jing W. Optimal orbit control strategy design for low energy moon return. In Proceedings of the 2015 27th Chinese Control and Decision Conference, CCDC 2015. Institute of Electrical and Electronics Engineers Inc. 2015. p. 2342-2346. 7162312. (Proceedings of the 2015 27th Chinese Control and Decision Conference, CCDC 2015). doi: 10.1109/CCDC.2015.7162312

Optimal orbit control strategy design for low energy moon return

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