Ares V Utilization in Support of a Human Mission to Mars

During the analysis cycles of Phase A-Cycle 3 (PA-C3) and the follow-on 8-wk minicycle of PA-C3', the Ares V team assessed the Ares V PA-C3D configuration to the Mars Design Reference Mission as defined in the Constellation Architecture Requirements Document and further described in Mars Design Reference Architecture 5.0 (DRA 5.0) that was publicly released in July 2009. The ability to support the reference approach for the crewed Mars mission was confirmed through this analysis (7-launch nuclear thermal propulsion (NTP) architecture) and the reference chemical approach as defined in DRA 5.0 (11- or 12-launch chemical propulsion module approach). Additional chemical propulsion options were defined that utilized additional technology investments (primarily in-space cryogenic propellant transfer) that allowed for the same mission to be accomplished with 9 launches rather than the 11 or 12, as documented in DRA 5.0 and associated follow-on activities. This nine-launch chemical propulsion approach showed a unique ability to decouple the architecture from major technological developments (such as zero-boiloff technology or the development of NTP stages) and allowed for a relaxing of the infrastructure investments required to support a very rapid launch rate (30-day launch spacing as documented in DRA 5.0). As an enhancing capability, it also shows promise in allowing for and incorporating the development of a commercial market for cryogenic propellant delivery on orbit, without placing such development on the critical path of beyond low-Earth orbit exploration. The ability of Ares V to support all of the aforementioned options and discussion of key forward work that is required to fully understand the complexities and challenges presented by the Mars mission is further documented herein.