### 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 language | English |
---|---|

Article number | 040011 |

Number of pages | 7 |

Journal | AIP Conference Proceedings |

Volume | 1959 |

Issue number | 1 |

DOIs | |

Publication status | Published - 2018 |

Event | International Scientific Conference on Mechanics: 8th Polyakhov's Reading - Saint Petersburg Duration: 29 Jan 2018 → 2 Feb 2018 |

### Scopus subject areas

- Physics and Astronomy(all)

### Cite this

*AIP Conference Proceedings*,

*1959*(1), [040011]. https://doi.org/10.1063/1.5034614

}

*AIP Conference Proceedings*, vol. 1959, no. 1, 040011. https://doi.org/10.1063/1.5034614

**Attitude stabilization of a spacecraft equipped with large electrostatic protection screens.** / Nikitin, D. Yu; Tikhonov, A. A.

Research output › › peer-review

TY - JOUR

T1 - Attitude stabilization of a spacecraft equipped with large electrostatic protection screens

AU - Nikitin, D. Yu

AU - Tikhonov, A. A.

PY - 2018

Y1 - 2018

N2 - 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.

AB - 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.

KW - ELECTRODYNAMIC STABILIZATION

KW - GEOMAGNETIC-FIELD

KW - LORENTZ-FORCE

KW - SATELLITES

KW - ORBITS

KW - MOTION

KW - SYSTEM

KW - EARTH

UR - http://www.scopus.com/inward/record.url?scp=85047214743&partnerID=8YFLogxK

U2 - 10.1063/1.5034614

DO - 10.1063/1.5034614

M3 - Article

VL - 1959

JO - AIP Conference Proceedings

JF - AIP Conference Proceedings

SN - 0094-243X

IS - 1

M1 - 040011

ER -