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Asymptotic stability of a satellite with electrodynamic attitude control in the orbital frame. / Aleksandrov, A. Yu; Tikhonov, A. A.

In: Acta Astronautica, Vol. 139, 01.10.2017, p. 122-129.

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

Harvard

Aleksandrov, AY & Tikhonov, AA 2017, 'Asymptotic stability of a satellite with electrodynamic attitude control in the orbital frame', Acta Astronautica, vol. 139, pp. 122-129. https://doi.org/10.1016/j.actaastro.2017.06.033

APA

Aleksandrov, A. Y., & Tikhonov, A. A. (2017). Asymptotic stability of a satellite with electrodynamic attitude control in the orbital frame. Acta Astronautica, 139, 122-129. https://doi.org/10.1016/j.actaastro.2017.06.033

Vancouver

Aleksandrov AY, Tikhonov AA. Asymptotic stability of a satellite with electrodynamic attitude control in the orbital frame. Acta Astronautica. 2017 Oct 1;139:122-129. https://doi.org/10.1016/j.actaastro.2017.06.033

Author

Aleksandrov, A. Yu ; Tikhonov, A. A. / Asymptotic stability of a satellite with electrodynamic attitude control in the orbital frame. In: Acta Astronautica. 2017 ; Vol. 139. pp. 122-129.

BibTeX

@article{72c83a82d95e4713a4b1300cfcdbda0a,
title = "Asymptotic stability of a satellite with electrodynamic attitude control in the orbital frame",
abstract = "A satellite in a circular near-Earth orbit is under consideration. The three-axis stabilization of the satellite in the orbital coordinate system with the use of electrodynamic attitude control system is studied. No constraints are imposed on the Earth's magnetic field approximation. The gravity gradient disturbing torque acting on the satellite attitude dynamics is taken into account as the largest disturbing torque. With the use of the Lyapunov direct method, conditions under which electrodynamic control solves the problem are obtained. The restrictions on the control parameter values for which one can guarantee the asymptotic stability of the programmed satellite motion are found and represented in an explicit form. Comparison of the results of numerical simulation and analytical investigation demonstrate effectiveness of the proposed approach.",
keywords = "Asymptotic stability, Attitude stabilization, Geomagnetic field, Satellite",
author = "Aleksandrov, {A. Yu} and Tikhonov, {A. A.}",
year = "2017",
month = oct,
day = "1",
doi = "10.1016/j.actaastro.2017.06.033",
language = "English",
volume = "139",
pages = "122--129",
journal = "Acta Astronautica",
issn = "0094-5765",
publisher = "Elsevier",

}

RIS

TY - JOUR

T1 - Asymptotic stability of a satellite with electrodynamic attitude control in the orbital frame

AU - Aleksandrov, A. Yu

AU - Tikhonov, A. A.

PY - 2017/10/1

Y1 - 2017/10/1

N2 - A satellite in a circular near-Earth orbit is under consideration. The three-axis stabilization of the satellite in the orbital coordinate system with the use of electrodynamic attitude control system is studied. No constraints are imposed on the Earth's magnetic field approximation. The gravity gradient disturbing torque acting on the satellite attitude dynamics is taken into account as the largest disturbing torque. With the use of the Lyapunov direct method, conditions under which electrodynamic control solves the problem are obtained. The restrictions on the control parameter values for which one can guarantee the asymptotic stability of the programmed satellite motion are found and represented in an explicit form. Comparison of the results of numerical simulation and analytical investigation demonstrate effectiveness of the proposed approach.

AB - A satellite in a circular near-Earth orbit is under consideration. The three-axis stabilization of the satellite in the orbital coordinate system with the use of electrodynamic attitude control system is studied. No constraints are imposed on the Earth's magnetic field approximation. The gravity gradient disturbing torque acting on the satellite attitude dynamics is taken into account as the largest disturbing torque. With the use of the Lyapunov direct method, conditions under which electrodynamic control solves the problem are obtained. The restrictions on the control parameter values for which one can guarantee the asymptotic stability of the programmed satellite motion are found and represented in an explicit form. Comparison of the results of numerical simulation and analytical investigation demonstrate effectiveness of the proposed approach.

KW - Asymptotic stability

KW - Attitude stabilization

KW - Geomagnetic field

KW - Satellite

UR - http://www.scopus.com/inward/record.url?scp=85021753646&partnerID=8YFLogxK

U2 - 10.1016/j.actaastro.2017.06.033

DO - 10.1016/j.actaastro.2017.06.033

M3 - Article

AN - SCOPUS:85021753646

VL - 139

SP - 122

EP - 129

JO - Acta Astronautica

JF - Acta Astronautica

SN - 0094-5765

ER -

ID: 9173476