Statistics – Applications
Scientific paper
Jan 2002
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2002aipc..608..617w&link_type=abstract
SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM- STAIF 2002. Conference on Thermophyiscs in Microgravity; Conference on In
Statistics
Applications
Propulsion Reactors, Magnetohydrodynamic Generators And Thermionic Convertors, Plasma Diodes, Spaceborne And Space Research Instruments, Apparatus, And Components
Scientific paper
Electric propulsion applications are enhanced by high power-to-mass ratios for their electric power sources. At multi-megawatt levels, we can expect thrust production systems to be less than 5 kg/kWe. Application of nuclear electric propulsion to human Mars missions becomes an attractive alternative to nuclear thermal propulsion if the propulsion system is less than about 10 kg/kWe. Recent references have projected megawatt-plus nuclear electric sources at specific mass values from less than 1 kg/kWe to about 5 kg/kWe. Various assumptions are made regarding power generation cycle (turbogenerator; MHD) and reactor heat source design. The present paper compares heat source and power generation options on the basis of a parametric model that emphasizes heat transfer design and realizable hardware concepts. Pressure drop (important!) is included in the power cycle analysis, and MHD and turbogenerator cycles arc compared. Results indicate that power source specific mass less than 5 kg/kWe is attainable, even if peak temperatures achievable are limited to 1500 K. Projections of specific mass less than 1 kg/kWe are unrealistic, even at the highest peak temperatures considered. .
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