Takaya Inamori
School of engineering, department of aerospace engineering, The University of Tokyo

Abstract

In recent years, a number of nano- and micro-satellites have been proposed for various objectives such as remote sensing and astronomy observations because of their practical cost and short development period. In most of these satellite missions, the satellite attitude should be stabilized precisely to obtain high resolution images and precise scientific data. To achieve such precise attitude control and stabilization, the satellite attitude dynamics should be precisely understood, both in their satellite design phase and in-orbit satellite operations. Specifically, a magnetic attitude torque is the dominant disturbance in Low Earth Orbit (LEO) for small sized satellites, although the magnetic torque is not significantly affected in usual sized satellites. The presentation will show examples of magnetic analyses in the development of the small sized satellites.