An isotope heat source integrated with a 7 kW/e/ to 25 kW/e/ Brayton cycle space power supply.The power system described is intended for applications in a manned space mission. The Isotope Reentry Vehicle (IRV) developed is considered together with the Heat Source (HS), the Heat Source Heat Exchanger and the Brayton Cycle Power Conversion Module. Other subjects discussed include the IRV/Brayton cycle spacecraft integration concept, abort and deorbit mechanization, emergency cooling methods, and crew shielding requirements. Mounting and integration for the IRV is to a large degree controlled by nuclear safety requirements. Another major factor in the installation concept is the type of emergency cooling or passive heat dump mode used in rejection of HS energy.
Document ID
19730041217
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Ryan, R. L.
Graham, J. W. (Avco Corp. Avco Systems Div., Wilmington, Mass., United States)
Coombs, M. G. (AiResearch Aviation Co. Los Angeles, Calif., United States)
Bloomfield, H. S. (NASA Lewis Research Center Cleveland, Ohio, United States)
Date Acquired
August 7, 2013
Publication Date
January 1, 1972
Subject Category
Auxiliary Systems
Meeting Information
Meeting: Intersociety Energy Conversion Engineering Conference; Energy 70