Dinamica de Atitude Para Satelites Estabilizados Por Rotacao (Attitude Dynamics for Satellites Stabilized Through Spin)

摘要

A simplified dynamic modelling for the attitude motion of spin stabilized artificial satellites is proposed. Torques due to induced magnetic fields on the satellite, eddy currents, and gravity gradient are considered. The corresponding Euler equations are developed in convenient coordinates and solved by numerical integration. The FORTRAN program, as well as a user's manual, examples of use, and listings are described.