Energy of a satellite going around the earth in an elliptical orbit is given by $-\frac{\mathrm{GMm}}{2\mathrm{a}}$ 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 $=\sqrt{\frac{3\mathrm{GM}}{5\mathrm{R}}}$ from a height h = R above the surface of the earth. Calculate its maximum distance from the centre of the earth.