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6.2 Deployable Structures 35 In the MOXIE system, oxygen is generated via carbon dioxide electrolysis at 800◦C in a solid oxide electrolyzer. The most obvious difference between the PEC approach and MOXIE is that the PEC device can potentially operate at much lower temperatures than MOXIE. Solid oxide electrolysis usually requires energy input of 25–35 kW (to produce 2.2 kg O2/hour) for electrolysis current and heat. For a production rate of 1 kg/h of oxygen, the non-aqueous PEC device theoretically requires 1000gO2 (1mol/32gO2)(4mole-/molO2)=125mole-/h, 125 mol e-/h (96480 C/mole e-) = 1206,000 C/h = 335 A, and thermodynamic power of 335 A × 1.33 V = 446 W. Total power required for 2.2 kg/h of oxygen will range from 13–27 kW. 6.2 Deployable Structures Each strategy discussed in this report for the in-situ generation of oxygen and fuels required for advanced robotic sample return missions or astronaut ascent from Mars requires the autonomous deployment of a lightweight structure that covers a large area on the Martian surface. For power- beaming energy from the Sun to the Martian surface in the form of microwaves as discussed below, a large structure is required, incorporating the light-gathering functions and chemical conversion elements. For aqueous or non-aqueous designs for PEC or integrated solar photovoltaic–EC processes, a light absorber component replaces the receiver on the Martian soil. A common theme among these concepts is a large-area device that can be robustly and reliably deployed to a given configuration and has feeds and collection ports for reactants and products of the electrochemical reactions, which at this time include molecules such as CO2, O2, CH4, H2O, CO, and H2. Although each technology has other certain specific requirements, this represents the minimum needs for a structure that must be deployed on large scales on Mars. Large deployable structures have been successfully deployed in space environments; for example, the U. S. segment of the International Space Station (ISS) includes eight unfoldable solar array wings, each measuring roughly 36 m × 12 m (Winslow, 1993). These wings are large, lightweight structures designed for the low-load microgravity environment in low Earth orbit. These characteristics are relevant to the power beaming application where deployment of a large solar photovoltaic array in Mars orbit is required to absorb sunlight and convert its energy into the form of microwaves that are re-radiated toward the Martian surface. A 60 m × 60 m deployable orbiting solar array and microwave energy transmitter has been designed at Caltech for use inPDF Image | ISRU Challenge Production of O2 and Fuel from CO2
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