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C. Pre-positioning H2O, 450 s ISP, Lunar L2 Departure: 2xSLS and 3x FH Launches It is possible to replace one of the SLS launches in the previous architecture with an additional two FH launches. As before, the first SLS launch places the transit habitat, solar array, and crew vehicle RCS to LL2. The second SLS launch delivers an LL2 depot with 48.5 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 delivers a drop tank of water to LL2 containing an additional 19 t of propellant. A third 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 three 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 LL2 is found in Table III-5, and a summary of the launch manifests in Table III-6. 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 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 Mars delivery has a glut of propellant for the return trip. When considering the projected remaining propellant from Mars orbit injection, and the possibility of discarding the solar array, under half of this propellant is needed for trans-Earth injection. Therefore, this architecture could support two consecutive Mars missions with only four SLS launches and five FH launches between them for the crew vehicle. With the payload design in this architecture, it is not quite possible to accomplish each mission with only two SLS launches and two FH launches, doing away with the LL2 FH depot. This could be achieved if the payload mass were only 3 t less, but propellant margins would be slim. It is easier to do this from HEO where the trans-Mars injection maneuver costs less V; see subsection E. Table III-5: 450 s, 2xSLS 3xFH Vehicle Summary Vehicle Element Mass (t) Propulsion Engine 6 Tank 1.64 Propellant 67.5 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 135.13 Table III-6: 450 s, 2xSLS 3xFH Launch Manifests Launch Manifest Mass (t) SLS Block 2 1 Transit Hab, Solar Array, RCS 49.4 to LL2 2 48.5 t of H2O delivered to LL2 50 to LL2 FH 1 14.4 t of H2O delivered to Mars orbit. 16 to Mars 2 19 t of H2O delivered to LL2 20 to LL2 3 6 crew in Orion MPCV, plus propulsion engine 16.6 Total Mass to Orbit 152 15 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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