Energy of a satellite going around the earth in an elliptical orbit is given by `-(GMm)/(2a)` where M and m are masses of the earth and the satellite respectively and 2a is the major axis of the elliptical path. A satellite is launched tangentially with a speed `sqrt((3GM)/(5R)` from a height h = R above the surface of the earth. Calculate its maximum
distance from the centre of the earth
