Space craft to solar system bodies must deal with multiple deviations under the in uence of gravity. The motion of satellite in one of the types of conic section strongly depends upon escape velocity. The goal of this paper is to nd the trajectory of satellite by analysing orbit's eccentricity and or-bital parameters. This paper also focuses on the derivation of general orbit equation from the base called Newton's law of motion and Newton's law of gravitation.
Eccentricity, Flight path angle, True anomaly, Perigee and Apogee radius, Trajectory
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