A spaceship is launched into a circular orbit close to the Earth's surface. What additional velocity has to be imparted to the spaceship to overcome the gravitational pull?

Explanation

`v_0=sqrt((gammaM)/(R))` and `v_e=sqrt((2gammaM)/(R))`
Thus the sought additional velocity
`Deltav=v_e-v_0=sqrt((gammaM)/(R))(sqrt2-1)=gR(sqrt2-1)`
This 'kick' in velocity must be given along the direction of motion of the satellite in its orbit.