A satellite is revolving around the earth with a kinetic energy E . The minimum addition of kinetic energy needed to make it escape from its orbit is

Step-by-step solution

(d): Orbital velocity of satellite, v₀= G M r Kinetic energy, E= 1 2 m v₀^2= 1 2 G M m r Kinetic energy for escaping, aligned E^ = 1 2 m v_e^2 & = 1 2 m 2 G M r = G M m r & =2 E ( v_e= 2 G M r ) aligned Additional kinetic energy needed =E^ -E=2 E-E=E