NASA is sending a remote-sensing spacecraft to Mars.

Given:

Earth parking orbit altitude= 1000 km

Mars Parking orbit altitude= 500 km

μ_Earth = 3.99×10⁵ km³/s²

μ_Mars = 4.280×10⁴ km³/s²

μ_Sun = 1.33×10¹¹ km³/s²

^{Earth’s orbital radius = 1.50 x108 km (assume Earth has a circular orbit for this problem)}

Mars’ orbital radius = 2.28 x10⁸ km (assume Mars has a circular orbit for this problem)

^{Find the semi major axis of the transfer orbit,}v_{∞Earth ,}v_∞Mars,ΔV_boost,^_ΔV_retro,ΔV_mission⁽