Attitude stabilization of a spacecraft equipped with large electrostatic protection screens

D. Yu Nikitin, A. A. Tikhonov

Research outputpeer-review

Abstract

A satellite with a system of three electrostatic radiation protection (ERP) screens is under consideration. The screens are constructed as electrostatically charged toroidal shields with characteristic size of order equal to 100 m. The interaction of electric charge with the Earth's magnetic field (EMF) give rise to the Lorentz torque acting upon a satellite attitude motion. As the sizes of ERP system are large, we derive the Lorentz torque taking into account the complex form of ERP screens and gradient of the EMF in the screen volume. It is assumed that the satellite center of charge coincides with the satellite mass center. The EMF is modeled by the straight magnetic dipole. In the paper we investigate the usage of Lorentz torque for passive attitude stabilization for satellite in a circular equatorial orbit. Mathematical model for attitude dynamics of a satellite equipped with ERP interacting with the EMF is derived and first integral of corresponding differential equations is constructed. The straight equilibrium position of the satellite in the orbital frame is found. Sufficient conditions for stability of satellite equilibrium position are constructed with the use of the first integral. The gravity gradient torque is taken into account. The satellite equilibrium stability domain is constructed.

Original languageEnglish
Article number040011
Number of pages7
JournalAIP Conference Proceedings
Volume1959
Issue number1
DOIs
Publication statusPublished - 2018
EventInternational Scientific Conference on Mechanics: 8th Polyakhov's Reading - Saint Petersburg
Duration: 29 Jan 20182 Feb 2018

Scopus subject areas

  • Physics and Astronomy(all)

Cite this

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abstract = "A satellite with a system of three electrostatic radiation protection (ERP) screens is under consideration. The screens are constructed as electrostatically charged toroidal shields with characteristic size of order equal to 100 m. The interaction of electric charge with the Earth's magnetic field (EMF) give rise to the Lorentz torque acting upon a satellite attitude motion. As the sizes of ERP system are large, we derive the Lorentz torque taking into account the complex form of ERP screens and gradient of the EMF in the screen volume. It is assumed that the satellite center of charge coincides with the satellite mass center. The EMF is modeled by the straight magnetic dipole. In the paper we investigate the usage of Lorentz torque for passive attitude stabilization for satellite in a circular equatorial orbit. Mathematical model for attitude dynamics of a satellite equipped with ERP interacting with the EMF is derived and first integral of corresponding differential equations is constructed. The straight equilibrium position of the satellite in the orbital frame is found. Sufficient conditions for stability of satellite equilibrium position are constructed with the use of the first integral. The gravity gradient torque is taken into account. The satellite equilibrium stability domain is constructed.",
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Attitude stabilization of a spacecraft equipped with large electrostatic protection screens. / Nikitin, D. Yu; Tikhonov, A. A.

In: AIP Conference Proceedings, Vol. 1959, No. 1, 040011, 2018.

Research outputpeer-review

TY - JOUR

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AU - Tikhonov, A. A.

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