A spacecraft is in a circular, equatorial orbit 1 or radius ro and speed vo about an unknown planet (Mu does not equal 398,600 km^3/s^2). At a point C it impulsively travels to orbit 2, for which the ascending node is point C, the eccentricity if 0.1, the inclination is 30 degrees and the argument for periapsis is 60 degrees. Calculate in terms of vo the single delta-v required for C for this maneuver.