A satellite of mass `m` is in an elliptical orbit around the earth. The speed of the satellite at its nearest position is `sqrt((6GM)//(5r))` where r is the perigee (nearest point) distance from the centre of the earth. It is desired to transfer the satellite to the circular orbit of radius equal to its apogee (farthest point) distance from the centre of the earth. The change in orbital speed required for this purpose is

A satellite of mass m is in an elliptical orbit around the earth. The speed of the satellite at its nearest position is (6GM)//(5r) where r is the perigee (nearest point) distance from the centre of the earth. It is desired to transfer the satellite to the circular orbit of radius equal to its apogee (farthest point) distance from the centre of the earth. The change in orbital speed required for this purpose is

A satellite of mass m is in an elliptical orbit around the earth of mass M(M gt gt m) the speed of the satellite at its nearest point ot the earth (perigee) is sqrt((6GM)/(5R)) where R= its closest distance to the earth it is desired to transfer this satellite into a circular orbit around the earth of radius equal its largest distance from the earth. Find the increase in its speed to be imparted at the apogee (farthest point on the elliptical orbit).

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