Heavy Lift Launch Vehicles with Existing Propulsion Systems
SpaceOps 2010 Conference<br><b><i>Delivering on the Dream</b></i><br><i>Hosted by NASA Mars AIAA 2010-2370 25 - 30 April 2010, Huntsville, Alabama Heavy Lift Launch Vehicles with Existing Propulsion Systems Benjamin Donahue1 Lee Brady2 Mike Farkas3 Shelley LeRoy4 Neal Graham5 Boeing Phantom Works, Huntsville, AL 35824 Doug Blue6 Boeing Space Exploration, Huntington Beach, CA 92605 This paper describes Heavy Lift Launch Vehicle concepts that are based on existing propulsion systems. Both In-Line and Sidemount configurations for Crew, Crew plus cargo and Cargo only missions are illustrated. Payload data includes launches to due East LEO, ISS, Trans-Lunar Injection (TLI) and the Earth-Sun L2 point. Engine options include SSME and RS-68 for the Core stage and J-2X and RL-10 engines for Upper stages. Heavy Lift would provide the large volumes and heavy masses required to enable high science return missions, while utilizing proven propulsion elements. I. Introduction Both In-line and Sidemount Heavy Lift Launch Vehicle (HLLV) concepts, utilizing Solid Rocket Booster (SRB) and Space Shuttle Main Engine (SSME) elements, would enable exploration missions1-6 that might otherwise be impractical with current launch vehicles. Potential missions and payloads (Fig. 1) include space telescopes, fuel depots, Mars, Venus, Europa, and Titan sample return vehicles, Crewed Lunar and Near Earth Object (NEO) vehicles, power beaming platforms and others. The use of existing main propulsion systems (SSME, RS-68 engines, SRBs) would minimize the upfront cost and shorten the time to initial operational capability (IOC) of any new HLLV as compared to a similar program with new propulsion elements.
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