Attitude dynamics and control of spacecraft using geomagnetic Lorentz force

Abstract

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.

Monoaxial Electrodynamic Stabilization of an Artificial Earth Satellite in the Orbital Coordinate System via Control With Distributed Delay

“…The concept of AES attitude control using the Lorentz torque was proposed in [4] and papers cited therein. Later this concept was addressed in [5], [6] and developed in accordance with modern trends in control theory. The electrodynamic attitude control strategy based on simultaneous usage of the magnetic and Lorentz torques occurred to be potent [7] since it can relief some natural constraints that are inherent to both magnetic and Lorentz attitude control systems.…”