Abstract

The dynamic equations for the motion of satellites with passive and semi-passive attitude stabilization are derived. As not only circular but also elliptic orbits are considered, differential equations with periodic coefficients are obtained. It is shown that the equations are considerably simplified if the independent variable “time” is replaced by the true anomaly Ω . Magnetic phenomena are discussed for passive and semi-passive attitude control. Methods are explained for the analysis of the resulting time-varying linear systems.

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