Low power DIPS design for NASA missions

Details Low power DIPS design for NASA missions Low power DIPS design for NASA missions

Jan 1991

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1991aipc..217..916j&link_type=abstract

Proceedings of the eighth symposium on space nuclear power systems. AIP Conference Proceedings, Volume 217, pp. 916-922 (1991).

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Lunar, Planetary, And Deep-Space Probes, Thermoelectric, Electrogasdynamic And Other Direct Energy Conversion

Scientific paper

Conceptual designs of low power dynamic isotope power systems (DIPS) for NASA's future deep space missions are being developed to characterize the power system's unique features in the 0.5-1.0 kilowatt-electric (kWe) range. The August 1990 Mariner Mark II spacecraft design was used for the spacecraft integration study. One basic design with slight mission specific variations was developed for the Cassini, Comet Nucleus Sample Return, and Outer Planet Orbiter Probe missions. A low power DIPS flight unit offers comparable specific power values to the MOD-RTG unit with a factor-of-three improvement in radioisotope fuel requirements. This was accomplished by fully exploiting the dynamic power conversion technology available in the DIPS program.

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