A spacecraft is in a circular, equatorial orbit 1 of radius r0 and speed v0 about an unknown planet (mu not equal to 398600). At point C it impulsively transfers to orbit 2, for which the ascending node is point C, the eccentricity is 0.1, the inclination is 30 degree and the argument of periapsis is 60 degree. Calculate, in terms of v0, the single delta v required at C for this maneuver.