There is a spaceship in a circular orbit close to Earth's surface. The additional velocity that should be imparted to the spaceship in orbit to overcome the gravitational pull is (Radius of Earth is 6400 km and $g=9.8{\mathrm{ms}}^{-2}\text{ ) }$

For orbiting the earth close to its surface

$=\frac{{\mathrm{mv}}^2}{\mathrm{R}}=\frac{\mathrm{GMm}}{{\mathrm{R}}^2},\mathrm{ie},{\mathrm{v}}_0=\sqrt{\frac{\mathrm{GM}}{\mathrm{R}}}$

$=\sqrt{\mathrm{gR}}$

$\therefore {\mathrm{v}}_0=\sqrt{\left(9.8\times 6.4\times {10}^6\right)}$

$=8 {\mathrm{kms}}^{-1}$

For escaping from close to the surface of earth

$\frac{\mathrm{GMm}}{\mathrm{R}}=\frac{1}{2}{\mathrm{mv}}_{\mathrm{t}}^2,{\mathrm{v}}_{\mathrm{e}}=\sqrt{\frac{2\mathrm{GM}}{\mathrm{R}}}=\sqrt{2\mathrm{gR}}$

$v_e=\sqrt{2}\times v_0=1.41\times 8{\mathrm{kms}}^{-1}$

$=11.2 {\mathrm{kms}}^{-1}$

$\therefore$   the additional velocity to be imparted to the orbiting satellite for escaping is

$11.2-8=3.2 {\mathrm{kms}}^{-1}$