Design a patched conic transfer trajectory from a circular Earth parking orbit with an altitude of 300 km, to an elliptical Mars arrival orbit with a periapsis of 5447 km and a semimajor axis of 8832 km. Draw three diagrams with adequate information (5pts each) corresponding to the three segments of the patched conic design. [Hint: Reuse the SOI calculated above to determine the patch point. Determine the excess speed from the international Hohmann transfer. Determine the maneuver at the periapsis of the hyperbolic orbit.]