http://arxiv.org/abs/1405.3542
Attitude Dynamics of a rigid artificial satellite subject to gravity gradient and Lorentz torques in a circular orbit is considered. Lorentz torque is developed on the basis of the electrodynamic effects of the Lorentz force acting on the charged satellite’s surface. We assume that the satellite is moving in Low Earth Orbit (LEO) in the geomagnetic field which is considered as a dipole model. Our model of the torque due to the Lorentz force is developed for a general shape of artificial satellite, and the nonlinear differential equations of Euler are used to describe its attitude orientation. All equilibrium positions are determined and {their} existence conditions are obtained. The numerical results show that the charge $q$ and radius $\rho_0$ of the charged center of satellite provide a certain type of semi passive control for the attitude of satellite. The technique for such kind of control would be to increase or decrease the electrostatic radiation screening of the satellite. The results {obtained} confirm that the change in charge can effect the magnitude of the Lorentz torque, which may affect the satellite’s control. Moreover, the relation between the magnitude of the Lorentz torque and inclination of the orbits is investigated.
Y. Abdel-Aziz and M. Shoaib
Thu, 15 May 14
27/55
Comments: To appear in Research in Astronomy and Astrophysics
You must be logged in to post a comment.