A spacecraft is in a heliocentric orbit trailing Earth. It is desired to perform a Hohmann transfer maneuver to enter a heliocentric orbit trailing Mars. Calculate the required propellant mass for this operation. The spacecraft has a dry mass of 5000 kg (excluding propellant for this maneuver) and an engine with an exhaust velocity of 4.4 km/s.

(Heliocentric trailing orbit means that this spacecraft is close to and trailing Earth or Mars, but actually orbiting the Sun, not these planets).

• μ Sun = 1.327 × 10E20 m3 / s2
• Earth's orbital radius = 1 AU
• Mars' orbital radius = 1.52 AU