Research on orbit maneuver strategy for electrodynamic tether satellite

Jian Zhang; Feng Wang; Zhao Wei Sun; Hua Yi Li

doi:10.3873/j.issn.1000-1328.2014.10.011

Research on orbit maneuver strategy for electrodynamic tether satellite

Jian Zhang
, Feng Wang^*
, Zhao Wei Sun
, Hua Yi Li

^*Corresponding author for this work

School of Astronautics

Harbin Institute of Technology
National and Local United Engineering Research Center of Small Satellite Technology

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

5 Scopus citations

Abstract

Three kinds of current control strategies have been used to accomplish orbit maneuvers of electrodynamic tether satellites. The constant current control strategy could change the orbit inclination without changing the right ascension of the ascending node; and the bang-bang current control strategy could change the right ascension of the ascending node without changing orbit inclination. At last, the time-varying current control strategy based on Fourier series is used to realize the general orbital maneuvers. To improve the control accuracy, the method named small error modification has been used. The simulations show that these control strategies could finish the desired orbit maneuvers.

Original language	English
Pages (from-to)	1182-1188
Number of pages	7
Journal	Yuhang Xuebao/Journal of Astronautics
Volume	35
Issue number	10
DOIs	https://doi.org/10.3873/j.issn.1000-1328.2014.10.011
State	Published - 30 Oct 2014

Keywords

Bang-bang current
Constant current
Electrodynamic tether satellite
Fourier current
Small error modification

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10.3873/j.issn.1000-1328.2014.10.011

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title = "Research on orbit maneuver strategy for electrodynamic tether satellite",

abstract = "Three kinds of current control strategies have been used to accomplish orbit maneuvers of electrodynamic tether satellites. The constant current control strategy could change the orbit inclination without changing the right ascension of the ascending node; and the bang-bang current control strategy could change the right ascension of the ascending node without changing orbit inclination. At last, the time-varying current control strategy based on Fourier series is used to realize the general orbital maneuvers. To improve the control accuracy, the method named small error modification has been used. The simulations show that these control strategies could finish the desired orbit maneuvers.",

keywords = "Bang-bang current, Constant current, Electrodynamic tether satellite, Fourier current, Small error modification",

author = "Jian Zhang and Feng Wang and Sun, \{Zhao Wei\} and Li, \{Hua Yi\}",

year = "2014",

month = oct,

day = "30",

doi = "10.3873/j.issn.1000-1328.2014.10.011",

language = "英语",

volume = "35",

pages = "1182--1188",

journal = "Yuhang Xuebao/Journal of Astronautics",

issn = "1000-1328",

publisher = "Chinese Society of Astronautics",

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TY - JOUR

T1 - Research on orbit maneuver strategy for electrodynamic tether satellite

AU - Zhang, Jian

AU - Wang, Feng

AU - Sun, Zhao Wei

AU - Li, Hua Yi

PY - 2014/10/30

Y1 - 2014/10/30

N2 - Three kinds of current control strategies have been used to accomplish orbit maneuvers of electrodynamic tether satellites. The constant current control strategy could change the orbit inclination without changing the right ascension of the ascending node; and the bang-bang current control strategy could change the right ascension of the ascending node without changing orbit inclination. At last, the time-varying current control strategy based on Fourier series is used to realize the general orbital maneuvers. To improve the control accuracy, the method named small error modification has been used. The simulations show that these control strategies could finish the desired orbit maneuvers.

AB - Three kinds of current control strategies have been used to accomplish orbit maneuvers of electrodynamic tether satellites. The constant current control strategy could change the orbit inclination without changing the right ascension of the ascending node; and the bang-bang current control strategy could change the right ascension of the ascending node without changing orbit inclination. At last, the time-varying current control strategy based on Fourier series is used to realize the general orbital maneuvers. To improve the control accuracy, the method named small error modification has been used. The simulations show that these control strategies could finish the desired orbit maneuvers.

KW - Bang-bang current

KW - Constant current

KW - Electrodynamic tether satellite

KW - Fourier current

KW - Small error modification

UR - https://www.scopus.com/pages/publications/84909965885

U2 - 10.3873/j.issn.1000-1328.2014.10.011

DO - 10.3873/j.issn.1000-1328.2014.10.011

M3 - 文章

AN - SCOPUS:84909965885

SN - 1000-1328

VL - 35

SP - 1182

EP - 1188

JO - Yuhang Xuebao/Journal of Astronautics

JF - Yuhang Xuebao/Journal of Astronautics

IS - 10

ER -

Research on orbit maneuver strategy for electrodynamic tether satellite

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Keywords

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