Electromagnetic effects on the orbital motion of a charged spacecraft

Abdel‐Aziz, Yehia A.; Khalil, Khalil Ibrahim

doi:10.1088/1674-4527/14/5/008

Cited by 12 publications

(5 citation statements)

References 8 publications

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“…1), Equation ( 22) impacts Equation ( 4 Eq. ( 33) of Abdel-Aziz & Khalil (2014) shows that, for polar orbits, the inclination is not affected by electric forces of dipolar origin.…”

Section: The Non-gravitational Perturbationsmentioning

confidence: 97%

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Measuring the De Sitter precession with a new Earth’s satellite to the $$\simeq 10^{-5}$$ ≃ 10 - 5 level: a proposal

Iorio¹

2019

Eur. Phys. J. C

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The inclination I of an Earth's satellite in polar orbit undergoes a secular De Sitter precession of −7.6 milliarcseconds per year for a suitable choice of the initial value of its non-circulating node Ω. The competing long-periodic harmonic rates of change of I due to the even and odd zonal harmonics of the geopotential vanish for either a circular or polar orbit, while no secular rates occur at all. This may open up, in principle, the possibility of measuring the geodesic precession in the weak-field limit with an accurately tracked satellite by improving the current bound of 9 × 10 −4 from Lunar Laser Ranging, which, on the other hand, may be even rather optimistic, by one order of magnitude, or, perhaps, even better. The most insidious competing effects are due to the solid and ocean components of the K 1 tide since their perturbations have nominal huge amplitudes and the same temporal pattern of the De Sitter signature. They vanish for polar orbits. Departures of ≃ 10 −5 − 10 −3 deg from the ideal polar geometry allow to keep the K 1 tidal perturbations to a sufficiently small level. Most of the other gravitational and non-gravitational perturbations vanish for the proposed orbital configuration, while the non-vanishing ones either have different temporal signatures with respect to the De Sitter effect or can be modeled with sufficient accuracy. In order to meet the proposed goal, the measurement accuracy of I should be better than ≃ 35 microarcseconds = 0.034 milliarcseconds over, say, 5 yr.

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“…1), Equation ( 22) impacts Equation ( 4 Eq. ( 33) of Abdel-Aziz & Khalil (2014) shows that, for polar orbits, the inclination is not affected by electric forces of dipolar origin.…”

Section: The Non-gravitational Perturbationsmentioning

confidence: 97%

“…The interaction between the Earth's magnetic field, assumed here dipolar and with its dipole moment m ⊕ aligned with the rotational axis, and the possible surface electric charge Q of the satellite induce long-term orbital perturbations (Abdel-Aziz & Khalil 2014). By means of Eq.…”

Section: The Non-gravitational Perturbationsmentioning

confidence: 99%

Measuring the De Sitter precession with a new Earth’s satellite to the $$\simeq 10^{-5}$$ ≃ 10 - 5 level: a proposal

Iorio¹

2019

Eur. Phys. J. C

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“…The dynamics of electrically charged satellites have been addressed employing Lagrange's planetary equations by several authors, as Sehnal (1969), Peck (2005), Abdel-Aziz (2007), Atchison & Peck (2009), Streetman & Peck (2009), Abdel-Aziz & Khalil (2014, Li (2016), Abd El-Salam et al (2017, Abd El-Bar & Abd El-Salam (2018), Tealib et al (2020). Using Lie series based on Kamel technique, Kamel (1970), the problem is treated differently and canonically.…”

Section: Introductionmentioning

confidence: 99%

Perturbations of Zonal and Tesseral Harmonics on Frozen Orbits of Charged Satellites

El-Salam,

Rahoma,

El-Saftawy

et al. 2024

J. Astron. Space Sci.

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The objective of this research is to address the issue of frozen orbits in charged satellites by incorporating geopotential zonal harmonics up to J6 and the initial tesseral harmonics. The employed model starts from the first normalized Hamiltonian to calculate specific sets of long-term frozen orbits for charged satellites. To explore the frozen orbits acquired, a MATHEMATICA CODE is developed. The investigation encompasses extensive variations in orbit altitudes by employing the orbital inclination and argument of periapsis as freezing parameters. The determined ranges ensuring frozen orbits are derived from the generated figures. Three-dimensional presentations illustrating the freezing inclination in relation to eccentricity, argument of periapsis, and semi-major axis parameters are presented. Additional three-dimensional representations of the phase space for the eccentricity vector and its projection onto the nonsingular plane are examined. In all investigated scenarios, the impacts of electromagnetic (EM) field perturbations on the freezing parameters of a charged satellite are demonstrated.

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“…Many authors introduced Lorentz force as perturbations on the orbital motion and formation flying such as in Vokrouhlicky (1989), Abdel-Aziz (2007a), Streetman and Peck (2007), Hiroshima et al (2009) , Gangestad et al (2010), andAbdel-Aziz andKhalil (2014). Abdel-Aziz (2007b) studied the attitude stabilization of rigid spacecraft moving in a circular orbit due to Lorentz torque in the case of uniform magnetic field and cylindrical shape of spacecraft. Yamakawa et al (2012) investigated the attitude motion of a charged pendulum spacecraft moving in circular orbit, having the shape of a dumbbell pendulum due to Lorentz torque.…”

Section: Introductionmentioning

confidence: 99%

“…Orbits of a spacecraft accelerated by the Lorentz force are termed Lorentz-augmented orbits, because the Lorentz force cannot completely replace traditional rocket propulsion. Many authors introduced using the Lorentz force to generate perturbations on the orbital motion and formation flying such as in Vokrouhlicky (1989), Abdel-Aziz (2007a), Streetman & Peck (2007), Hiroshi et al (2009), Gangestad et al (2010) and Abdel-Aziz & Khalil (2014). Abdel-Aziz (2007b) studied the attitude stabilization of a rigid spacecraft moving in a circular orbit due to Lorentz torque in the case of a uniform magnetic field and a spacecraft having a cylindrical shape.…”

Section: Introductionmentioning

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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Electromagnetic effects on the orbital motion of a charged spacecraft

Cited by 12 publications

References 8 publications

Measuring the De Sitter precession with a new Earth’s satellite to the $$\simeq 10^{-5}$$ ≃ 10 - 5 level: a proposal

Measuring the De Sitter precession with a new Earth’s satellite to the $$\simeq 10^{-5}$$ ≃ 10 - 5 level: a proposal

Perturbations of Zonal and Tesseral Harmonics on Frozen Orbits of Charged Satellites

Attitude dynamics and control of spacecraft using geomagnetic Lorentz force

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