The Effects of an Induced Electric Dipole Moment due to Earth’s Electric Field on the Artificial Satellites Orbit

Heilmann, Armando; Ferreira, Luiz Danilo Damasceno; Dartora, C. A.

doi:10.1007/s13538-012-0058-1

Cited by 5 publications

(4 citation statements)

References 11 publications

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“…In the literature, investigations concerning to calculations of orbits and astronomical observables associated to them have been considered in many contexts with very sophisticated theoretical frameworks [9][10][11][12], including aspects like either the sensibility to disturbances in the orbit of satellites [9] or the study of equatorial circular orbits in static axially symmetric gravitating systems [10] and the calculation of radius of the orbits as well. In general, relativistic frameworks have been used [11,12].…”

Section: Introductionmentioning

confidence: 99%

Geometrical aspects of Venus transit

Bertuola

Frajuca

Magalhães

et al. 2015

Rev. Bras. Ensino Fís.

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Section: Introductionmentioning

confidence: 99%

Geometrical aspects of Venus transit

Bertuola

Frajuca

Magalhães

et al. 2015

Rev. Bras. Ensino Fís.

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“…Now we develop the Lorentz force experienced by electric field F elec . According to Ulaby (2005) and Heilmann et al (2012) we can write the electric force as follows.…”

Section: Total Torque Due To Lorentz Forcementioning

confidence: 99%

Attitude dynamics and control of spacecraft using geomagnetic Lorentz force

Abdel‐Aziz

Shoaib

2015

Res. Astron. Astrophys.

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The attitude stabilization of a charged rigid spacecraft in Low Earth Orbit (LEO) using torques due to Lorentz force in pitch and roll directions is considered. A spacecraft that generates an electrostatic charge on its surface in the Earth magnetic field will be subject to perturbations from Lorentz force. The Lorentz force acting on an electrostatically charged spacecraft may provide a useful thrust for controlling a spacecraft's orientation. We assume that the spacecraft is moving in the Earth's magnetic field in an elliptical orbit under the effects of the gravitational, geomagnetic and Lorentz torques. The magnetic field of the Earth is modeled as a non-tilted dipole. A model incorporating all Lorentz torques as a function of orbital elements has been developed on the basis of electric and magnetic fields. The stability of the spacecraft orientation is investigated both analytically and numerically. The existence and stability of equilibrium positions is investigated for different values of the charge to mass ratio (α * ). Stable orbits are identified for various values of α * . The main parameters for stabilization of the spacecraft are α * and the difference between the components of the moment of inertia of spacecraft.

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“…Now we develop the Lorentz force due to the electric field F elec . According to Ulaby (2005) and Heilmann et al (2012) we can write the electric force as the following:…”

Section: The Total Lorentz Forcementioning

confidence: 99%

Electromagnetic effects on the orbital motion of a charged spacecraft

Abdel‐Aziz

Khalil

2014

Res. Astron. Astrophys.

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This paper deals with the effects of electromagnetic forces on the orbital motion of a spacecraft. The electrostatic charge which a spacecraft generates on its surface in the Earth's magnetic field will be subject to a perturbative Lorentz force. A model incorporating all Lorentz forces as a function of orbital elements has been developed on the basis of magnetic and electric fields. This Lorentz force can be used to modify or perturb the spacecraft's orbits. Lagrange's planetary equations in the Gauss variational form are derived using the Lorentz force as a perturbation to a Keplerian orbit. Our approach incorporates orbital inclination and the true anomaly. The numerical results of Lagrange's planetary equations for some operational satellites show that the perturbation in the orbital elements of the spacecraft is a second order perturbation for a certain value of charge. The effect of the Lorentz force due to its magnetic component is three times that of the Lorentz force due to its electric component. In addition, the numerical results confirm that the strong effects are due to the Lorentz force in a polar orbit, which is consistent with realistic physical phenomena that occur in polar orbits. The results confirm that the magnitude of the Lorentz force depends on the amount of charge. This means that we can use artificial charging to create a force to control the attitude and orbital motion of a spacecraft.

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The Effects of an Induced Electric Dipole Moment due to Earth’s Electric Field on the Artificial Satellites Orbit

Cited by 5 publications

References 11 publications

Geometrical aspects of Venus transit

Geometrical aspects of Venus transit

Attitude dynamics and control of spacecraft using geomagnetic Lorentz force

Electromagnetic effects on the orbital motion of a charged spacecraft

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