Design of Space Powerplants |
Contents
TEMPERATURE CONTROL FOR LUNAR VEHICLES | 1 |
RADIATION HEAT TRANSFER FROM EXTENDED | 28 |
Design Procedures | 47 |
Copyright | |
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aluminum ammonia analysis analyzed approximately Assumed conditions available energy Brayton cycle Btu/lb Carnot cycle cent Combining Eqs compressor computed condenser area configuration factor curves data of Fig determined direct cycle duct effectiveness enthalpy Entropy environment Environmental parameter equal equation evaluated extended surfaces fin length fluid cycle fluid parameter Freon ft/kw gases heat exchanger heat rejected heat transfer heat-transfer higher hydrogen ideal fluid increase kilowatt latent heat lunar mercury Methyl chloride Minimum radiator area mixture nondimensional obtained plate plotted potassium power requirements powerplant thermal efficiency problem profile number propellant psia Rankine cycle reduced root thickness rubidium saturated liquid saturated vapor shown in Fig sodium solar specific heat superheat T₁ T₂ Teff Temperature parameter temperature ratio theoretical profile thermal efficiency tube turbine efficiency turbine exhaust Turbine inlet temperature Turbine Rankine efficiency unit of heat vapor cycles vapor pressure weight zero