Abstract Logistics supply chains with nodes at critical locations such as the Earth’s surface, Earth’s orbit, cis-lunar space, Mars orbit and the surface of Mars are crucial to enable sustainable human exploration of Mars. The concept of a Mars orbital logistics node is envisaged to have at least aggregation, refueling, resupply and refurbishing capabilities is defined in this paper. Its elements are analogous to platforms like the International Space Station and Lunar Gateway. The stationing orbit of the logistics node is one of the primary design drivers in determining the associated propellant requirement. We evaluate $\Delta$V requirements across four phases of the mission—interplanetary transfer, capture and departure, deorbit and entry, and launch and orbit transfer. A comprehensive data base of interplanetary trajectories is analyzed. Perturbations due to Mars’ gravity are considered and multiple options for maneuver are considered herein. Three mission scenarios – long stay crewed, short stay crewed and cargo transfer – are evaluated along with three deorbit concepts. A broad range of Low Mars Orbits (LMO) with periods between 0.4 and 0.6 sols and Highly Elliptical Mars Orbits (HEMO) with periods between 2 and 4 sols is found to fall on the trade-off curve of total $\Delta$V and orbital periods across seven synodic periods. Final orbit selection can be made using this data and a desired criteria and mission timeline. For example, HEMO minimizes propellant to access the stationing orbit from interplanetary trajectory whereas LMO minimizes propellant requirement to access the surface from the stationing orbit. HMO is also favorable for short stay and cargo missions.

Highlights • Mars orbital logistics node enables robust logistics planning for human exploration. • LMO, HMO and HEMO orbits analyzed as stationing orbit options for the logistics node. • Ballistic and low-thrust interplanetary trajectories over 7 synodic periods analyzed. • Criteria based on weighted $\Delta$V for different mission variables affect orbit selection.