An earth satellite is in an elliptical orbit with the perigee at 600 km altitude and an eccentricity of e = 0.866. Determine the parameters of the new satellite trajectory, if a rocket propulsion system is fired in the direction of flight giving an incremental velocity of 200 m/sec when
(a) fired at apogee,
(b) fired at perigee, and
(c) fired at perigee, but in the opposite direction, reducing the velocity.