Q3: A satellite is in a circular earth orbit of altitude 300 km executes a Hohmann transfer to a coplanar circular earth orbit of altitude 3000 km, calculate: a) [1.5 marks] eccentricity, specific angular momentum, semi major axis, of the Hohmann elliptical transfer orbit. b) [1 mark] the total delta-v required for the Hohmann transfer c) [0.5 mark] the transfer orbit time. A02 401 300 km 1 3000 km