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

Результат исследований: Научные публикации в периодических изданияхстатья

2 Цитирования (Scopus)

Выдержка

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.

Язык оригиналаанглийский
Страницы (с-по)122-129
Число страниц8
ЖурналActa Astronautica
Том139
DOI
СостояниеОпубликовано - 1 окт 2017

Отпечаток

Attitude Control
Attitude control
Electrodynamics
Asymptotic stability
Asymptotic Stability
Satellites
Torque
Earth (planet)
Lyapunov Direct Method
Control Parameter
Gravity
Gravitation
Orbits
Stabilization
Orbit
Magnetic Field
Control System
Magnetic fields
Gradient
Restriction

Предметные области Scopus

  • Авиакосмическая техника
  • Прикладная математика

Цитировать

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

В: Acta Astronautica, Том 139, 01.10.2017, стр. 122-129.

Результат исследований: Научные публикации в периодических изданияхстатья

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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

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