ISRU Challenge Production of O2 and Fuel from CO2

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ISRU Challenge Production of O2 and Fuel from CO2 ( isru-challenge-production-o2-and-fuel-from-co2 )

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40 Chapter 6. System-Level Considerations Figure 6.4: Monolithic deployable structure variant of the Venetian blind structure, akin to an inflatable air mattress. 6.3 Thermal Management In this section, thermal management of a notional PEC system is considered, with rough order- of-magnitude estimates. We assume a PEC system with active area of 160 m2 on the Martian surface. Under light dust loading, the system receives a sunlit average incident power of 556 W/m2 throughout the Martian year, or 152 W/m2 over the Martian sol (27% capacity factor, assuming flat plate configuration; D. Kass, personal communiation, 2016). With 10% of incident light lost due to reflection and/or dust, and 10% solar-to-fuel conversion efficiency, 50 W/m2 is converted to chemical bonds, leaving 450 W/m2 of thermal gain. We further assume 50% Faradaic efficiency for the desired product, but that is not pertinent to thermal management. Assuming operation at 290 K, and low-emissivity coatings in the mid-infrared (􏰖10 μm wavelength) of 5% for both top and bottom PEC surfaces, Stefan-Boltzman radiative losses are 20 W/m2 from each surface, or 40 W/m2 overall. Polished metal surfaces offer emissivities as low as 􏰖3%; we assume the back surface has one of these. We also assume that a well-designed broadband coating on the top surface can achieve a similar emissivity, though the state-of-the-art is not known. Additional thermal gain from sky and ground radiation is calculated as follows. Average mid- latitude sunlit air temperatures are assumed to be 250 K, with nighttime temperatures of 200 K.

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