NASA LogoNTRSNTRS - NASA Technical Reports ServerSearchmore_vertCollectionsAboutNewsHelpLogin Back to ResultsRobust Exploration and Commercial Missions to the Moon Using Nuclear Thermal Rocket Propulsion and Lunar Liquid Oxygen Derived from FeO-Rich Pyroclasitc DepositsThe nuclear thermal rocket (NTR) has frequently been identified as a key space asset required for the human exploration of Mars. This proven technology can also provide the affordable access through cislunar space necessary for commercial development and sustained human presence on the Moon. It is a demonstrated technology capable of generating both high thrust and high specific impulse (I(sub sp) approx. 900 s) twice that of today's best chemical rockets. Nuclear lunar transfer vehicles-consisting of a propulsion stage using three approx. 16.5-klb(sub f) small nuclear rocket engines (SNREs), an in-line propellant tank, plus the payload-are reusable, enabling a variety of lunar missions. These include cargo delivery and crewed lunar landing missions. Even weeklong ''tourism'' missions carrying passengers into lunar orbit for a day of sightseeing and picture taking are possible. The NTR can play an important role in the next phase of lunar exploration and development by providing a robust in-space lunar transportation system (LTS) that can allow initial outposts to evolve into settlements supported by a variety of commercial activities such as in-situ propellant production used to supply strategically located propellant depots and transportation nodes. The use of lunar liquid oxygen (LLO2) derived from iron oxide (FeO)-rich volcanic glass beads, found in numerous pyroclastic deposits on the Moon, can significantly reduce the launch mass requirements from Earth by enabling reusable, surface-based lunar landing vehicles (LLVs)that use liquid oxygen and hydrogen (LO2/LH2) chemical rocket engines. Afterwards, a LO2/LH2 propellant depot can be established in lunar equatorial orbit to supply the LTS. At this point a modified version of the conventional NTR-called the LO2-augmented NTR, or LANTR-is introduced into the LTS allowing bipropellant operation and leveraging the mission benefits of refueling with lunar-derived propellants for Earth return. The bipropellant LANTR engine utilizes the large divergent section of its nozzle as an ''afterburner'' into which oxygen is injected and supersonically combusted with nuclear preheated hydrogen emerging from the engine's choked sonic throat-essentially ''scramjet propulsion in reverse.'' By varying the oxygen-to-hydrogen mixture ratio, LANTR engines can operate over a range of thrust and I(sub sp) values while the reactor core power level remains relatively constant. A LANTR-based LTS offers unique mission capabilities including short-transit-time crewed cargo transports. Even a ''commuter'' shuttle service may be possible allowing ''one-way'' trip times to and from the Moon on the order of 36 hours or less. If only 1% of the extracted LLO2 propellant from identified resource sites were available for use in lunar orbit, such a supply could support daily commuter flights to the Moon for many thousands of years! This report outlines an evolutionary architecture and examines a variety of mission types and transfer vehicle designs, along with the increasing demands on LLO2 production as mission complexity and velocity change delta V requirements increase. A comparison of vehicle features and engine operating characteristics, for both NTR and LANTR engines, is also provided along with a discussion of the propellant production and mining requirements associated with using FeO-rich volcanic glass as source material.Document ID20180002979Acquisition SourceGlenn Research CenterDocument TypeTechnical Memorandum (TM)AuthorsBorowski, Stanley K.*(NASA Glenn Research Center Cleveland, OH, United States)*Ryan, Stephen W.*(NASA Glenn Research Center Cleveland, OH, United States)*Burke, Laura M.*(NASA Glenn Research Center Cleveland, OH, United States)*McCurdy, David R.*(Vantage Partners, LLC Cleveland, OH, United States)*Fittje, James E.*(Vantage Partners, LLC Cleveland, OH, United States)*Joyner, Claude R.*(Aerojet Rocketdyne, Inc. West Palm Beach, FL, United States)*Date AcquiredMay 21, 2018Publication DateApril 1, 2018Subject CategoryLunar And Planetary Science And ExplorationPropellants And FuelsReport/Patent NumberE-19452GRC-E-DAA-TN47489NASA/TM-2018-219725AIAA Paper 2017-4938Meeting InformationMeeting: Propulsion and Energy Forum and ExhibitionLocation: Atlanta, GACountry: United StatesStart Date: July 10, 2017End Date: July 12, 2017Sponsors:American Inst. of Aeronautics and AstronauticsFunding Number(s)CONTRACT_GRANT: NNC12BA01BWBS: WBS 894614.04.03.01Distribution LimitsPublicCopyrightPublic Use Permitted.Keywordsrocketnuclear thermal propulsionSpacecraft designAvailable DownloadsNameType20180002979.pdfSTIcloud_downloadcontent_copyvisibilityRelated RecordsThere are no records associated with this record.visibility_offNo Preview Available
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