Application of thermionic SNPS with thermal reactor for spacecraft orbital transfer mission

Conference · Sat Jan 05 00:00:00 EST 1991 · AIP Conference Proceedings (American Institute of Physics); (United States)

DOI:https://doi.org/10.1063/1.40118· OSTI ID:5475930

Andreev, P V; Gryaznov, G M; Zhabotinsky, E E; Nikonov, A M; Serbin, V I ^[1]

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1. SPU Krasnaya Zvezda'' USSR, Moscow 115230 (SU)

The region of expedient using of SNPS with in-core thermal thermionic reactor (ITR) is limited by electric power level of about 100 kWe under SNPS lifetime from 3 to 5 years. At the same time the reactor power may be forced from two to three times during the period of about half a year. The mathematical model of SNPS mass dependence on a degree of forcing is given. The results of calculation of payload masses and transfer times for transfer from low orbit to geostationary orbit for two thermal reactors having emission area 1.6 m{sup 2} and 2.5 m{sup 2} are given for different types of electrojets.

• OSTI ID: 5475930
• Report Number(s): CONF-910116-; CODEN: APCPC
• Journal Information: AIP Conference Proceedings (American Institute of Physics); (United States), Vol. 217:2; Conference: 8. symposium on space nuclear power systems, Albuquerque, NM (United States), 6-10 Jan 1991; ISSN 0094-243X
• Country of Publication: United States
• Language: English

Related Subjects

30 DIRECT ENERGY CONVERSION
THERMIONIC REACTORS
MATHEMATICAL MODELS
ORBITS
SPACE VEHICLES
THERMIONIC FUEL ELEMENTS
TOPAZ REACTOR
EXPERIMENTAL REACTORS
FUEL ELEMENTS
HYDRIDE MODERATED REACTORS
POWER REACTORS
REACTOR COMPONENTS
REACTORS
RESEARCH AND TEST REACTORS
VEHICLES
NESDPS Office of Nuclear Energy Space and Defense Power Systems
300401* - Thermionic Converters- Design & Development