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E. Pre-positioning H2O, 450 s ISP, HEO Departure, 2xSLS and 2xFH Launches It is possible to replace one of the SLS launches in the previous architecture with an additional FH launch. As before, the first SLS launch places the transit habitat, solar array, and crew vehicle RCS to HEO. The second SLS launch delivers an HEO depot with 47.5 t of propellant. The crew are delivered in an Orion MPCV by a FH launch, along with the crew vehicle engine. A second FH launch, chronologically the first, delivers 14.4 t of water to Mars orbit for the return trip. This delivery is performed concurrently with two other cargo vehicles sent the preceding launch window to the crew mission. The complete mission is accomplished with only two SLS launches and two FH launches. The cost savings of this depends on the cost of an individual SLS launch; as discussed in the next section, this should be at least $500M. A summary of the vehicle at departure from HEO is found in Table III-9, and a summary of the launch manifests in Table III-10. When the propellant for the return trip is finished electrolyzing, the majority of the solar panels can be jettisoned to improve the mass ratio for the trans-Earth injection maneuver. Their excess power is no longer be needed at this point. This is not necessary to accomplish the maneuver, but it reduces the propellant which must be taken from the Mars depot. The propellant reduction is not enough to help support a second mission without another FH propellant delivery, but it improves the propellant margin. Table III-9: 450 s, 2xSLS+2xFH Vehicle Summary Vehicle Element Mass (t) Propulsion Engine 6 Tank 1.64 Propellant 47.5 RCS 3 Total Module Mass 59.13 Number of Modules 1.0 Total Stage Mass 59.13 Payload Transit Habitat 41.3 CM+Crew 10.6 Solar Array 5.1 Total Vehicle Mass 115.13 Table III-10: 450 s, 2xSLS+2xFH Launch Manifests Launch Manifest Mass (t) SLS Block 2 1 Transit Hab, Solar Array, RCS 49.4 to HEO 2 48.5 t of H2O delivered to HEO 50 to HEO FH 1 14.4 t of H2O delivered to Mars orbit. 16 to Mars 2 6 crew in Orion MPCV, plus propulsion engine 16.6 Total Mass to Orbit 132 17 American Institute of Aeronautics and Astronautics Downloaded by NASA LANGLEY RESEARCH CENTRE on January 30, 2018 | http://arc.aiaa.org | DOI: 10.2514/6.2018-1537PDF Image | Water Electrolysis for Propulsion of a Crewed Mars
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