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Author:

Liu Yue (Liu Yue.) | Qian Yingjing (Qian Yingjing.) (Scholars:钱霙婧) | Ma Lin (Ma Lin.) | Jing Wuxing (Jing Wuxing.)

Indexed by:

CPCI-S

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.

Keyword:

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

Author Community:

  • [ 1 ] [Liu Yue]DEII Satellite Co Ltd, Beijing 100094, Peoples R China
  • [ 2 ] [Ma Lin]DEII Satellite Co Ltd, Beijing 100094, Peoples R China
  • [ 3 ] [Qian Yingjing]Beijing Univ Technol, Beijing 100022, Peoples R China
  • [ 4 ] [Jing Wuxing]Harbin Inst Technol, Harbin 150001, Peoples R China

Reprint Author's Address:

  • [Liu Yue]DEII Satellite Co Ltd, Beijing 100094, Peoples R China

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Source :

2015 27TH CHINESE CONTROL AND DECISION CONFERENCE (CCDC)

ISSN: 1948-9439

Year: 2015

Page: 2342-2346

Language: English

Cited Count:

WoS CC Cited Count: 2

SCOPUS Cited Count:

ESI Highly Cited Papers on the List: 0 Unfold All

WanFang Cited Count:

Chinese Cited Count:

30 Days PV: 1

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