A satellite is moving in a circular orbit round the earth with a diameter of orbit 2R . At a certain point a rocket fixed to the satellite is fired such that it increases the velocity of the satellite tangentially. The resulting orbit of the satellite would be

• A

  the particle will emerge from the other end with velocity $\sqrt{\frac{G{M}_e}{2R_e}}$, where M_e and R_e are earth's mass and radius, respectively

• B

  circular orbit with diameter greater than 2R

• C

  elliptical orbit with minimum distance from the earth equal to R

• D

  elliptical orbit with maximum distance from the earth equal to R