DEVELOPMENT OF GENERAL HEAT PUMP HEAT PIPE AND RANKINE POWER COMPONENTS FOR SPACECRAFT HEAT REJECTION SYSTEMS

FUTURE MILITARY SPACE MISSIONS WILL INTRODUCE SIGNIFICANT NEW TECHNOLOGICAL NEEDS FOR SPACECRAFT ENERGY SYSTEMS. VARIOUS TECHNOLOGIES NEED TO BE EVALUATED TO DETERMINE THE BEST TECHNOLOGY FOR A PARTICULAR APPLICATION. A DESIGN TOOL THAT ALLOWS RAPID BUT ACCURATE COMPARISON OF ALL ALTERNATIVES WOULD BE EXTREMELY USEFUL. THE INTENT OF THIS PROPOSAL IS TO EXTEND THE GENERALIZED SIM TOOL TRANSIENT MODELING CAPABILITY INTO HEAT PUMP, HEAT PIPE AND RANKINE HEAT ENGINE COMPONENTS, TO ENHANCE THE PREDICTION OF SPACECRAFT TWO-PHASE THERMAL MANAGEMENT DESIGN ALTERNATIVES, ENHANCE THE PREDICTION OF COMPONENT FAILURES, AND ENHANCE THE PREDICTION OF SPACECRAFT SYSTEM SURVIVABILITY AND MAINTAINABILITY. TWO-PHASE FLUID PROPERTIES FROM THE LITERATURE WILL BE USED TO CREATE ALGORITHMS FOR SATURATED AND SUPERHEATED PROPERTIES OF R113 AND R114. IN ADDITION, THE MODIFIED REDLICH WONG EQUATION OF STATE WILL BE USED TO DEVELOP THERMODYNAMIC MODELS FOR NON-AZEOTROPE BINARY MIXTURES OF R11, R113, AND R114.