Zero Boil-Off System Design and Thermal Analysis of the Bimodal Thermal Nuclear Rocket

Details Zero Boil-Off System Design and Thermal Analysis of the Bimodal Thermal Nuclear Rocket Zero Boil-Off System Design and Thermal Analysis of the Bimodal Thermal Nuclear Rocket

Jan 2006

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2006aipc..813..494c&link_type=abstract

SPACE TECH.& APPLIC.INT.FORUM-STAIF 2006: 10th Conf Thermophys Applic Microgravity; 23rd Symp Space Nucl Pwr & Propulsion; 4th C

Physics

Propulsion Reactors, Spaceborne And Space Research Instruments, Apparatus, And Components

Scientific paper

Mars exploration studies at NASA are evaluating vehicles that incorporate Bimodal Nuclear Thermal Rocket (BNTR) propulsion which use a high temperature nuclear fission reactor and hydrogen to produce thermal propulsion. The hydrogen propellant is to be stored in liquid state for periods up to 18 months. To prevent boil-off of the liquid hydrogen, a system of passive and active components are needed to prevent heat from entering the tanks and to remove any heat that does. This report describes the design of the system components used for the BNTR Crew Transfer Vehicle and the thermal analysis performed. The results show that Zero Boil-Off (ZBO) can be achieved with the electrical power allocated for the ZBO system.

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