Assuming planar orbits, calculate the hohmann transfer δv required and time of flight to transfer from a low earth circular orbit at a radius of 6628 km to the orbit of the moon (assume 60 earth radii). compare the hohmann δv with the δv of a three-maneuver strategy of (1) escaping to infinity on a parabolic orbit, (2) maneuvering from infinity to to approach the moon’s radius on a tangent path, and (3) circularizing at the moon orbital radius.