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F. Pre-positioning H2O, 450 s ISP, HEO Departure, 0xSLS and 5x/6xFH Launches It is possible to completely replace the SLS launches with FH launches. The first FH launch delivers a propulsion module with the engine and 55 t of propellant to LEO. The second FH launch delivers a boost to bring this module to HEO. The third FH launch delivers the transit habitat, solar array, RCS, and Orion MPCV with the crew to LEO. A fourth FH launch is used to boost this payload to HEO. A fifth FH launch delivers a depot with 14.4 t of propellant to Mars orbit. It may be desirable to launch the Orion MPCV later, after the other modules have been boosted to HEO and assembled. In this case, this architecture requires six FH launches instead of five. The cost-effectiveness of this depends on the exact costs of SLS and FH, which are further discussed in the next section. A summary of the vehicle is found in Table II-11, and a summary of the launch manifests in Table II-12. 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 available. Table III-7: 450 s, 5x/6xFH Vehicle Summary Vehicle Element Mass (t) Propulsion Engine 6 Tank 1.5 Propellant 55 RCS 3 Total Module Mass 65.5 Number of Modules 1.0 Total Stage Mass 65.5 Payload Transit Habitat 41.3 CM+Crew 10.6 Solar Array 5.1 Total Vehicle Mass 122.5 Table III-8: 450 s, 5x/6xFH Launch Manifests Launch Manifest Mass (t) FH 1 Propulsion module to LEO. 62.5 2 Boosting #1 to HEO. (Equivalent of 63.8 at LEO) 3 Other crew vehicle elements to LEO. 57 if including Orion, 46.4 otherwise 4 Boosting #3 to HEO. (Equivalent of 63.8 at LEO) 5 14.4 t of H2O delivered to Mars orbit. 16 to Mars 6 (If needed) Orion MPCV delivery 0 or 10.6 to HEO Total Mass to Orbit 263.1 18 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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