Abstract
An expression for the thermal efficiency of a surface used as a receiver for spacecraft solar-power generation is derived in terms of the solar absorptance, hemispherical emittance, and concentration ratio. Experimental equipment is described in which direct measurements may be made up to 1000°C by using a carbon-arc-image furnace to simulate the sun. Emittance and absorptance data are presented on six polished metals and four plasma flame sprayed coatings from 200 to 800°C. It is shown that thermal conversion efficiencies as high as 40 percent at 800°C can be realized with refractory coatings and with a solar radiation concentration ratio of 50 or 6.9 watts per square centimeter.
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