Safe, Compact Nuclear Propulsion: Solid Core Nuclear Propulsion Concept
Abstract
The NERVA nuclear rocket engine was compared to an advanced nuclear electric engine as well as an advanced chemical engine for use in orbital transfer, and lunar and Mars missions. The NERVA stage had advantages over the chemical stage in payload, life cycle cost, and propellant consumption. The NERVA stage also had lower mission time requirements and life cycle cost compared to the nuclear electric stage. Fabrication of the NERVA stage does not require an extensive engine development program and demonstrated engine operating characteristics assure a reliable, flexible stage with a multiple mission capability. The single propellant used in nuclear engines eliminates the combustion hazards associated with the use of dual propellants in space. Preliminary evaluations also indicated that varying the tankage used according to mission could reduce the cost of operating the nuclear engine. The open air engine tests used to develop the NERVA fuel and engine system are not environmentally acceptable today. A proposed alternate fuel development approach is to screen candidate fuel systems and conduct failure tests in test reactors. Such testing facilities are designed for testing of closed loop systems. Failure tests on full scale core segments could also be conducted closed loop in larger facilities. A full scale engine system qualification could be accomplished but the facility must be designed to shut down immediately at the first detection of fission product release. It is estimated that all non-nuclear components of the NERVA engine system could be qualified for engine testing within four years and depending on the problems encountered, cost could range from $55 to $180 million.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1988
- Accession Number
- ADA202339
Entities
People
- Gerry Farbman
- Jack H. Ramsthaler
- Paul Harris
- Tal Sulmeisters