NASA LogoNTRSNTRS - NASA Technical Reports ServerSearchmore_vertCollectionsAboutNewsHelpLogin Back to ResultsVehicle and Mission Design Options for the Human Exploration of Mars/Phobos Using "Bimodal" NTR and LANTR PropulsionThe nuclear thermal rocket (NTR) is one of the leading propulsion options for future human missions to Mars because of its high specific impulse (Isp-850-1000 s) capability and its attractive engine thrust-to-weight ratio (approximately equal 3-10). To stay within the available mass and payload volume limits of a "Magnum" heavy lift vehicle, a high performance propulsion system is required for trans-Mars injection (TMI). An expendable TMI stage, powered by three 15 thousand pounds force (klbf) NTR engines is currently under consideration by NASA for its Design Reference Mission (DRM). However, because of the miniscule burnup of enriched uranium-235 during the Earth departure phase (approximately 10 grams out of 33 kilograms in each NTR core), disposal of the TMI stage and its engines after a single use is a costly and inefficient use of this high performance stage. By reconfiguring the engines for both propulsive thrust and modest power generation (referred to as "bimodal" operation), a robust, multiple burn, "power-rich" stage with propulsive Mars capture and reuse capability is possible, A family of modular "bimodal" NTR (BNTR) vehicles are described which utilize a common "core" stage powered by three 15 klbf BNTRs that produce 50 kWe of total electrical power for crew life support, an active refrigeration / reliquification system for long term, "zero-boiloff" liquid hydrogen (LH2) storage, and high data rate communications. An innovative, spine-like "saddle truss" design connects the core stage and payload element and is open underneath to allow supplemental "in-line" propellant tanks and contingency crew consumables to be easily jettisoned to improve vehicle performance. A "modified" DRM using BNTR transfer vehicles requires fewer transportation system elements, reduces IMLEO and mission risk, and simplifies space operations. By taking the next logical step--use of the BNTR for propulsive capture of all payload elements into Mars orbit--the power available in Mars orbit grows to 150 kWe compared to 30 kWe for the DRM. Propulsive capture also eliminates the complex, higher risk aerobraking and capture maneuver which is replaced by a simpler reentry using a standardized, lower mass "aerodescent" shell. The attractiveness of the "all BNTR" option is further increased by the substitution of the lightweight, inflatable "TransHab" module in place of the heavier, hard-shell hab module. Use of TransHab introduces the potential for propulsive recovery and reuse of the BNTR/ERV. It also allows the crew to travel to and from Mar on the same BNTR transfer vehicle thereby cutting the duration of the ERV mission in half--from approximately 4.7 to 2.5 years. Finally, for difficult Mars options, such as Phobos rendezvous and sample return missions, volume (not mass) constraints limit the performance of the "all LH2" BNTR stage. The use of "LOX-augmented" NTR (LANTR) engines, operating at a modest oxygen-to-hydrogen mixutre ratio (MR) of 0.5, helps to increase "bulk" propellant density and total thrust during the TMI burn. On all subsequent burns, the bimodal LANTR engines operate on LH2 only (MR=0) to maximize vehicle performance while staying within the lift capability of two Magnum launches.Document ID19990019002Acquisition SourceGlenn Research CenterDocument TypeTechnical Memorandum (TM)AuthorsStanley K Borowski*(Lewis Research Center Cleveland, OH, United States)*Leonard A Dudzinski*(Lewis Research Center Cleveland, OH, United States)*Melissa L McGuire*(Analex Fairfax, Virginia, United States)*Date AcquiredSeptember 6, 2013Publication DateDecember 1, 1998Publication InformationPublisher: National Aeronautics and Space AdministrationSubject CategorySpacecraft Propulsion And PowerReport/Patent NumberE-11445AIAA Paper 98-3883NAS 1.15:208834NASA/TM-1998-208834Meeting InformationMeeting: 34th Joint Propulsion ConferenceLocation: Cleveland, OHCountry: USStart Date: July 13, 1998End Date: July 15, 1998Sponsors:American Society of Mechanical Engineers,American Society For Engineering Education,American Institute of Aeronautics and Astronautics,Society of Automotive Engineers InternationalFunding Number(s)CONTRACT_GRANT: NAS3-27186PROJECT: RTOP 906-43-0ADistribution LimitsPublicCopyrightPublic Use Permitted.KeywordsNuclear thermal rocketNTRLOX–augmented NTRLANTRBimodalIn-situ resource utilizationHigh thrustNuclear propulsionMarsPhobosSpacecraftAvailable DownloadsNameType19990019002.pdfSTIcloud_downloadcontent_copyvisibilityRelated RecordsIDRelationTitle20030014643See AlsoVehicle and Mission Design Options for the Human Exploration of Mars/Phobos Using "Bimodal" NTR and LANTR Propulsionvisibility_offNo Preview Available
 No Fear Act | Freedom of Information Act | Office of the Inspector General | Agency Financial ReportsNASA Web Privacy Policy and Important Notices | NASA Guidelines for Quality of InformationDisclaimers, Copyright, Terms of Use | Accessibility | NASA OCIO | USA.gov | NASA.govContact Us | Site MapSTI LogoNASA Official: JoAnne R. Calhoun Site Curator: STI Compliance and Distribution Services Last Modified: September 12, 2024