Hohmann Transfer Trajectory to Mars: Fuel Optimization and Aerocapture Strategy

This paper presents the design and analysis of an interplanetary mission to Mars using a Hohmann transfer trajectory and aerocapture maneuver for orbital insertion around Mars. This mission architecture aims to reduce the total ΔV requirements by substituting a traditional propulsive Martian orbital insertion maneuver with an aerocapture maneuver. The mission will also utilize a novel high eccentricity parallel elliptical parking orbit around Earth for additional ΔV savings. Results demonstrate that significant ΔV reductions are achievable through this approach, enhancing overall mission efficiency and potentially allowing for an expansion of spacecraft capabilities.