Comparison of evolving photovoltaic and nuclear power systems for earth orbital applicationsPhotovoltaic and fission reactor orbital power systems are compared in terms of the end-to-end system power-to-mass ratios. Three PV systems are examined, i.e., a solid substrate with a cell array and a NiCd battery, a modified SEP array and an NiH2 battery, and a 62-micron Si cell array and a fuel cell. All arrays were modeled to be 13.5% efficient and to produce 25 kW dc. The SP-100 reactor consists of the heat source, radiation shield, heat pipes to transfer thermal energy from the reactor to thermoelectric elements, and a waste heat radiator. Consideration is given to system applications in orbits ranging from LEO to GEO, and to mission durations of 1, 5, and 10 yr. PV systems are concluded to be flight-proven, useful out of radiation belts, and best for low to moderate power levels. Limitations exist for operations where atmospheric drag may become a factor and due to the size of a large PV power supply. Space nuclear reactors will continue under development and uses at high power levels and in low altitude orbits are foreseen.
Document ID
19830045913
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Rockey, D. E. (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Jones, R. M. (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Schulman, I. (California Institute of Technology, Jet Propulsion Laboratory, Pasadena CA, United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1982
Subject Category
Spacecraft Propulsion And Power
Meeting Information
Meeting: IECEC ''82; Seventeenth Intersociety Energy Conversion Engineering Conference