The attitude stabilization of a charged rigid spacecraft in Low Earth Orbit(LEO) using torques due to Lorentz force in pitch and roll directions isconsidered. A spacecraft that generates an electrostatic charge on its surfacein the Earth magnetic field will be subject to perturbations from Lorentzforce. The Lorentz force acting on an electrostatically charged spacecraft mayprovide a useful thrust for controlling a spacecraft's orientation. We assumethat the spacecraft is moving in the Earth's magnetic field in an ellipticalorbit under the effects of the gravitational, geomagnetic and Lorentz torques.The magnetic field of the Earth is modeled as a non-tilted dipole. A modelincorporating all Lorentz torques as a function of orbital elements has beendeveloped on the basis of electric and magnetic fields. The stability of thespacecraft orientation is investigated both analytically and numerically. Theexistence and stability of equilibrium positions is investigated for differentvalues of the charge to mass ratio ($\alpha^*$). Stable orbits are identifiedfor various values of $\alpha^*$. The main parameters for stabilization of thespacecraft are $\alpha^*$ and the difference between the components of themoment of inertia of spacecraft.
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