A small RTG for future planetary missions

Journal Article · Wed Jan 01 04:00:00 EST 1997 · AIP Conference Proceedings

DOI:https://doi.org/10.1063/1.52134· OSTI ID:627651

Cockfield, R D; Kull, R A ^[1]

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1. Lockheed Martin Missiles Space P.O. Box 8555 Philadelphia, Pennsylvania19101 (United States)

A design study was conducted to characterize conceptual designs for a small Radioisotope Thermoelectric Generator (RTG), one that might be suitable for future planetary missions. Conceptual design configurations were derived from the General Purpose Heat Source{emdash}RTG (GPHS-RTG), with the design goal of providing 70 watts of electrical power at the end of a ten year mission life. Design improvements for mass minimization were evaluated, considering also the technical risk of the corresponding engineering development required. It was concluded that an RTG mass of 18 kg could be achieved with moderate risk. Further studies are recommended to define in detail the testing and other development activities that would be required to bring the conceptual design for such an RTG to reality. {copyright} {ital 1997 American Institute of Physics.}

• Sponsoring Organization: USDOE
• OSTI ID: 627651
• Report Number(s): CONF-970115--
• Journal Information: AIP Conference Proceedings, Journal Name: AIP Conference Proceedings Journal Issue: 1 Vol. 387; ISSN 0094-243X; ISSN APCPCS
• Country of Publication: United States
• Language: English

Related Subjects

30 DIRECT ENERGY CONVERSION
42 ENGINEERING
DESIGN
MASS
NESDPS Office of Nuclear Energy Space and Defense Power Systems
PERFORMANCE
POWER RANGE 10-100 W
RADIOISOTOPE HEAT SOURCES
SPACE VEHICLES
THERMOELECTRIC GENERATORS