Principles of attitude control of artificial satellites

Abstract

The equations of attitude motion are derived for small angular displacements from the equilibrium position of an earth-pointing satellite employing reaction-flywheel damping. This is followed by a discussion on the attitude control of a space-stabilised satellite, with particular reference to attitude control against the gravitational torque due to the earth and the use of reaction-jets for the control of a spherical satellite configuration; finally a single-plane analytical account is given, of a method of eliminating any undesirable angular momentum which the satellite may possess immediately it leaves the carrier missile for its future orbit.