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Heat transfer model for an open‐cycle gas core nuclear rocket
dc.contributor.authorPoston, David I.en_US
dc.contributor.authorKammash, Terry B.en_US
dc.date.accessioned2011-11-15T16:02:15Z
dc.date.available2011-11-15T16:02:15Z
dc.date.issued1992-01-15en_US
dc.identifier.citationPoston, David I.; Kammash, Terry (1992). "Heat transfer model for an open‐cycle gas core nuclear rocket." AIP Conference Proceedings 246(1): 1083-1088. <http://hdl.handle.net/2027.42/87494>en_US
dc.identifier.otherAPCPCS-246-1en_US
dc.identifier.urihttps://hdl.handle.net/2027.42/87494
dc.description.abstractA heat transfer model is developed to assess the propulsion capability of the open‐cycle gas core nuclear rocket. The model is used to determine the maximum specific impulse achievable without violating the wall material temperature and heat flux limits. For a 3000 MW reactor with a wall heat flux limit of 100 MW/m2, it is shown that a specific impulse of 3160 s and a thrust of 125 kN can be obtained.en_US
dc.publisherThe American Institute of Physicsen_US
dc.rights© The American Institute of Physicsen_US
dc.titleHeat transfer model for an open‐cycle gas core nuclear rocketen_US
dc.typeArticleen_US
dc.subject.hlbsecondlevelPhysicsen_US
dc.subject.hlbtoplevelScienceen_US
dc.description.peerreviewedPeer Revieweden_US
dc.contributor.affiliationumDept. of Nuclear Engineering, University of Michigan, Ann Arbor, MI 48109en_US
dc.description.bitstreamurlhttp://deepblue.lib.umich.edu/bitstream/2027.42/87494/2/1083_1.pdf
dc.identifier.doi10.1063/1.41764en_US
dc.identifier.sourceProceedings of the ninth symposium on space nuclear power systemsen_US
dc.owningcollnamePhysics, Department of


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