DOI: 10.21276/sjpms.2019.6.3.4

Pages: 42-52

This paper mainly deals with the trajectory of a near-Earth satellite constrained to move in a great-circle plane by means of a propulsion system contained in it. The vector equations of motion of the satellite with respect to a rectangular frame rigidly fixed to the surface of the Earth are formed. Its trajectory relative to the rotating Earth is analyzed taking into consideration that it is acted on by two forces: gravitational force and coriolis force; the aerodynamic forces being very small are neglected. The component of the coriolis force perpendicular to the greatcircle plane is balanced by the side thrust generated in the satellite at all time instants. Two numerical examples related to an elliptic orbit and a circular orbit respectively is cited. The centrifugal force being very small compared to the coriolis force is also neglected. Finally, an approximate formula has been derived to determine the drift of a satellite from its initial plane, ie, great-circle plane, if it is allowed to move freely for a short interval of time compared to its orbital period, ie, the satellite propulsion is shut off during that interval of time and the magnitude of deflection caused by the coriolis force has been numerically found in two cases