Radioisotope Power Systems for Space Applications

The results of a Douglas sponsored study of radioisotope secondary power-generating systems for space applications are presented. The study results are applicable to various space vehicles and missions requiring 4 kw or more of electrical power. The first generation of manned vehicles where a radioisotope power system is potentially applicable include the Extended Apollo and MOL type earth-orbiting laboratories. For this reason, the study results were applied to selecting a radioisotope power system for a small manned orbiting laboratory. The laboratory considered is capable of being launched in the post-1968 time period by a Titan 3C booster. An argon Brayton cycle, Dowtherm A Rankine cycle, and thermoelectric systems were investigated as possible secondary power systems capable of generating 4 kw of electrical power for the vehicle subsystem. Tradeoffs in weight, radiator-area requirement, development risk and isotope availability and cost were performed for the various systems. On the basis of the tradeoffs and the 4-kw design load, the argon Brayton cycle system was recommended.

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Mass-Based Optimization of Thermal Management and Power Systems for Space Applications

Journal of Propulsion and Power ◽

10.2514/2.6074 ◽

2002 ◽

Vol 18 (6) ◽

pp. 1161-1169 ◽

Cited By ~ 1

Author(s):

K. D. Freudenberg ◽

W. E. Lear ◽

S. A. Sherif ◽

E. L. Golliher

Keyword(s):

Power Systems ◽

Thermal Management ◽

Space Applications

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Advanced Solar Dynamic Space Power Systems, Part II: Detailed Design and Specific Parameters Optimization

Journal of Solar Energy Engineering ◽

10.1115/1.2847837 ◽

1995 ◽

Vol 117 (4) ◽

pp. 274-281 ◽

Cited By ~ 8

Author(s):

A. Agazzani ◽

A. Massardo

Keyword(s):

Power Systems ◽

Performance Optimization ◽

Optimization Procedure ◽

Specific Area ◽

Combined Cycle ◽

Parameters Optimization ◽

Space Applications ◽

Detailed Design ◽

Binary Cycle ◽

Space Power Systems

The aim of this work is the proposal and the analysis of advanced solar dynamic space power systems for electrical space power generation. In the first part of this work (Agazzani and Massardo, 1995) a performance optimization procedure for a SDCC (Solar Dynamic Combined Cycle) and a SDBC (Solar Dynamic Binary Cycle) was presented. Results have pointed out improvements obtainable in terms of conversion efficiency and specific area (m2/kWe), this last estimated in a simplified way. Nevertheless, before drawing conclusions about the superiority of these advanced systems, it is necessary to verify the constructive possibility of the single components of the systems, estimating weights and surfaces, the most significant parameters in space applications. In this second part the design procedures of some components will be discussed in detail; a complete optimization procedure (thermodynamic analysis and detailed design) will be presented with the purpose of minimizing specific area (m2/kWe) and specific mass (kg/kWe). The results obtained are presented, discussed, and compared with the data of a reference optimized CBC system (Massardo, 1993b).

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