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TEMPERATURE CONTROL FOR LUNAR VEHICLES
RADIATION HEAT TRANSFER FROM EXTENDED
23 other sections not shown
ammonia analysis analyzed approximately assumed available energy Brayton cycle Btu/hr Btu/lb Carnot cycle cent Combining Eqs compressor computed configuration factor cooling curves data of Fig decomposition determined differential direct cycle duct effectiveness emissivity engine enthalpy Entropy environment environmental parameter equal equations evaluated extended surfaces fin length fluid cycle fluid parameter free space Freon gases heat exchanger heat of solution heat radiated heat rejected heat transfer heat-transfer higher hydrazine hydrogen increase latent heat lithium hydride lunar mercury mixture monopropellants moon nondimensional obtained plotted powerplant prime mover problem profile number propellant Rankine cycle reduced refrigeration root thickness rubidium saturated vapor selected shown in Fig solar space vehicle specific heat storage Substituting superheat temperature control theoretical profile thermal efficiency triangular fin tube turbine efficiency Turbine inlet temperature vapor pressure vertical surface wall temperature weight zero