(a) With a single delta-v maneuver, the earth orbit of a satellite is to be changed from a circle of radius 15,000 km to a collinear ellipse with perigee altitude of 500 km and apogee radius of 22,000 km. Calculate the magnitude of the required delta-v and the change in the flight path angle Dg.
(b) What is the minimum total delta-v if the orbit change is accomplished instead by a Hohmann transfer?