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A method of semipassive attitude stabilization of a spacecraft in the geomagnetic field. / Tikhonov, A.A.

в: Cosmic Research, Том 41, № 1, 2003, стр. 63-73.

Результаты исследований: Научные публикации в периодических изданиях › статья › Рецензирование

Harvard

Tikhonov, AA 2003, 'A method of semipassive attitude stabilization of a spacecraft in the geomagnetic field', Cosmic Research, Том. 41, № 1, стр. 63-73. https://doi.org/10.1023/A:1022355730291

APA

Tikhonov, A. A. (2003). A method of semipassive attitude stabilization of a spacecraft in the geomagnetic field. Cosmic Research, 41(1), 63-73. https://doi.org/10.1023/A:1022355730291

Vancouver

Tikhonov AA. A method of semipassive attitude stabilization of a spacecraft in the geomagnetic field. Cosmic Research. 2003;41(1):63-73. https://doi.org/10.1023/A:1022355730291

Author

Tikhonov, A.A. / A method of semipassive attitude stabilization of a spacecraft in the geomagnetic field. в: Cosmic Research. 2003 ; Том 41, № 1. стр. 63-73.

BibTeX

@article{6c26849522b7434e8ead580e59ca6c7f,
title = "A method of semipassive attitude stabilization of a spacecraft in the geomagnetic field",
abstract = "A method is proposed that enables one to accomplish semipassive attitude stabilization of a spacecraft moving in a circular Keplerian orbit in the geomagnetic field. The method is developed on the basis of the electrodynamic effect of the influence of the Lorentz forces acting on the charged spacecraft's surface. It possesses advantages such as control law simplicity, reliability, cost efficiency, small mass, and the possibility of using the basic control system components not only for attitude stabilization of a spacecraft but also for ensuring its electrostatic radiation screening. The possibility of implementing the method for slightly inclined orbits is proved analytically. Two versions of implementation of the method are proposed. The calculations confirmed the possibility of using also these versions for orbits whose inclinations are not small. The advantages of each version are revealed and practical recommendations for their utilization are given.",
author = "A.A. Tikhonov",
year = "2003",
doi = "10.1023/A:1022355730291",
language = "Английский",
volume = "41",
pages = "63--73",
journal = "Cosmic Research",
issn = "0010-9525",
publisher = "МАИК {"}Наука/Интерпериодика{"}",
number = "1",

}

RIS

TY - JOUR

T1 - A method of semipassive attitude stabilization of a spacecraft in the geomagnetic field

AU - Tikhonov, A.A.

PY - 2003

Y1 - 2003

N2 - A method is proposed that enables one to accomplish semipassive attitude stabilization of a spacecraft moving in a circular Keplerian orbit in the geomagnetic field. The method is developed on the basis of the electrodynamic effect of the influence of the Lorentz forces acting on the charged spacecraft's surface. It possesses advantages such as control law simplicity, reliability, cost efficiency, small mass, and the possibility of using the basic control system components not only for attitude stabilization of a spacecraft but also for ensuring its electrostatic radiation screening. The possibility of implementing the method for slightly inclined orbits is proved analytically. Two versions of implementation of the method are proposed. The calculations confirmed the possibility of using also these versions for orbits whose inclinations are not small. The advantages of each version are revealed and practical recommendations for their utilization are given.

AB - A method is proposed that enables one to accomplish semipassive attitude stabilization of a spacecraft moving in a circular Keplerian orbit in the geomagnetic field. The method is developed on the basis of the electrodynamic effect of the influence of the Lorentz forces acting on the charged spacecraft's surface. It possesses advantages such as control law simplicity, reliability, cost efficiency, small mass, and the possibility of using the basic control system components not only for attitude stabilization of a spacecraft but also for ensuring its electrostatic radiation screening. The possibility of implementing the method for slightly inclined orbits is proved analytically. Two versions of implementation of the method are proposed. The calculations confirmed the possibility of using also these versions for orbits whose inclinations are not small. The advantages of each version are revealed and practical recommendations for their utilization are given.

U2 - 10.1023/A:1022355730291

DO - 10.1023/A:1022355730291

M3 - статья

VL - 41

SP - 63

EP - 73

JO - Cosmic Research

JF - Cosmic Research

SN - 0010-9525

IS - 1

ER -

ID: 5184877