Analysis of the Orbital Transfer between the Earth–Mars Orbit using Electric Propulsion based on the Direct Collocation Method

Abstract

This paper discusses a transfer system between the Earth and Mars orbit using electric propulsion under the assumption of launching the H-IIA launch vehicle on a one-way trip. The spacecraft was assumed to be launched into the geocentric orbit, then transferred to the Earth's heliocentric orbit using electric propulsion or a kick motor, and further transferred to Mars revolving orbit using electric propulsion. The dependency of the payload mass on the specific impulse of the propulsion and launch system were investigated by performing orbit optimization based on the direct collocation method. As a result, the most suitable transfer method to Mars orbit was the combination of a kick motor from the geostationary transfer orbit to the Earth's heliocentric orbit, and subsequently the use of electric propulsion to transverse to Mars orbit with C₃ = 9 km²/s². The maximum payload mass was 1,500 kg for a specific impulse of 3,000s.