Author : Pawan Prakash Dabeer and Sagar B ManeDeshmukh

This paper addresses the application of Lagrangian Mechanics for the determination of time required for reentry of the low orbiting satellites into the earth’s atmosphere. The Lagrangian approach takes gravitational force, drag force and kinetic energy into account for reentry of low orbiting satellite. Lagrangian mechanics investigates the effect of atmospheric drag on the motion of satellites in low Earth orbits. Investigation of reentry enables to determine the intervals when the satellite is to be fired back to its original orbit. The Cartesian coordinate system and polar coordinate system is used as reference frame for writing equations of motion then it is transformed to general coordinate system for application of Lagrangian equation of motion. The similar principle can be applied for the determination of reentry of space junk and low orbiting satellites and the prior risk on earth because of reentry of the same can be examined and controlled. It is important to determine the reentry rate of satellite so that it functions its desired application efficiently when it is orbiting at the predefined orbit at the time of its launch.

Keywords: Lagrangian Equation, Reentry Rate, Low Earth Orbiting Satellite.

Article published in International Journal of Current Engineering and Technology, Vol.6, No.5 (Oct-2016)