AN EVALUATION AND COMPARISON OF POWER SYSTEMS FOR LONG-DURATION, MANNED SPACE VEHICLES.
Abstract
This report presents the results of an analysis to evaluate and compare the application of space power systems to long-duration, manned space vehicles. From 2 to 10 kilowatts of average power is the range of interest for future manned military spacecraft. Such spacecraft will operate also at orbital altitudes below 200 n mi and may have orbital lifetimes of up to five yr. Six types of power systems (fuel cell, solar-photovoltaic, solar-dynamic, radioisotope-thermoelectric, radioisotope-dynamic, and nuclear reactor-dynamic) were evaluated for possible application to such missions. Evaluation and comparison criteria for a typical space mission included weight, development costs, operational costs, potential reliability, and spacecraft integration factors. It was concluded from this study that radioisotope-dynamic power systems are best for the range of applications being considered in this report. Radioisotope-thermoelectric systems have a high inherent reliability, but are heavier than radioisotope-dynamic systems. Fuel cell systems are too heavy and incurred excessive cost for resupply for long-duration missions. Solar-powered systems are not competitive because of excessive weight and difficult integration problems. Nuclear reactor systems are not competitive because of excessive weight, high costs, and poor mission integration characteristics. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1967
- Accession Number
- AD0820856
Entities
People
- Harrison J. Killian
- John G. Krisilas
Organizations
- The Aerospace Corporation