Solid Oxide Electrolysis System Optimization for Lunar Production of H2 and O2 (2021)

Remote sensing spacecraft have located extensive surface ice in lunar permanently shadowed regions (PSRs) associated with craters near the poles. Producing H 2 and O 2 propellants from icy regolith in these regions requires development of integrated, robust electrolysis systems capable of operating in cryogenic environments. This team is demonstrating the feasibility of propellant production from lunar ice using high-temperature solid-oxide electrolysis (SOXE) and an optimized integrated balance-of-plant (BOP). High-temperature steam electrolysis has an efficiency advantage over PEM and alkaline electrolyzers, requiring less than 45 kWh elec kg H2 -1 [1], much less than liquid-phase electrolysis. SOXE systems require efficient steam generation and compression, heat recuperation, and subsequent drying of the H 2 product stream. In this study, optimization of a demonstration system using less than 4.0 kW elec is based on OxEon’s SOXE stack that can deliver exceptionally high steam-utilization, ( U H2O &gt; 95%) and direct electrochemical O 2 compression to facilitate O 2 liquification with passive cooling at lunar PSR temperatures. This optimization forms the basis for the implementation of a lab-scale system for testing in a cryo-vac chamber, in order to demonstrate the viability of the optimized system for potential further, flight-scale development. The SOXE stack utilizes rare-earth stabilized zirconia electrolyte similar to technology in the MOXIE (Mars Oxygen In-Situ Resource Utilization Experiment) system [2]. The stack operates at 800ºC to balance trade-offs between area-specific resistance (ASR) and degradation. The 800ºC operating temperature requires efficient thermal integration of BOP to minimize specific energy and mass for reliable operation in the PSRs’ ‘cryo-vac’ conditions, where temperatures can reach as low as 40 K. This study shows how high U H2O enables optimization of the BOP components for system designs that can operate in the cryo-vacuum conditions with specific power w sp &lt; 45 kWh elec kg H2 -1 . Figure 1a illustrates principal BOP components including a steam generator, a compressor, cathode and anode heat recuperators, and a H 2 cooler/dryer. Passive radiative coolers for lunar operation prepare exhaust O 2 and H 2 product streams for liquification. The team developed a MATLAB-based process model to optimize the system configuration and operation. Performance of the stack, heat exchangers, and compressor are parameterized with both design parameters and system operating conditions that served as optimization variables. The system model is called by the MATLAB function ‘fmincon’ to minimize w sp under constraints that maintain reasonable system mass. The optimization study fixes H 2 production rate at 0.075 kg H 2 h -1 for the demonstration system in the lab-scale cryo-vac chamber. Optimization variables n this study for this lab-scale prototype system include 1) SOXE stack steam utilization U H2O ; 2) SOXE stack anode electrochemical compression D P a , for the O 2 exhaust pressure; 3) steam generator vapor outlet temperature T vap ; 4) compressor (scroll) pressure ratio P rat ; and 5) inlet steam mass-flow split between recuperators. The SOXE electrolysis stack has a fixed cell area (110.8 cm 2 ) and an experimentally measured area specific resistance (ASR). An electric preheater for the flow out of the cathode recuperator set the inlet steam flow to the 800 ℃ operating temperature, and this preheater added to the power (and thus specific work) required for the system. The SOXE cell operates at the thermoneutral voltage ( V tn ≈ 1.28 V/cell @ 800℃) and stack current I tot is proportional to ( V tn – V OCV )/ASR, where V OCV , open-circuit voltage, increases with U H2O . Primary BOP power demands include the compressor motor, SOXE stack steam preheater, thermal enclosure heater, and supplemental electric heating for the steam generator, but overall, the stack represented more than 80% of total power demand. Optimization of the system operating at 0.075 kg H 2 h -1 shows that w sp had the highest sensitivity to U H2O with values above 0.85 required to achieve w sp &lt; 45 kWh elec kg H2 -1 as shown in the contour plots of Figures 1b and 1c. Minimizing w sp encourages lower compressor pressure ratios P rat which is limited to a minimum of 2.0. Increasing the steam generator temperature reduces compressor power demand but increases supplemental electrical heating for the steam generation, Thus, steam generator outlet temperature has minimal impact on w sp as shown in Figure 1c. Electrochemical compression of the O 2 anode product does not benefit w sp , but it will greatly reduce the O 2 passive cooler size which reduces mass/costs for a lunar deployed system. Additional studies are ongoing to look at trade-offs between system mass and system power with an eye toward optimizing both cost and reliability in a full-scale lunar deployed system. References Poszdeich, K. Schwarze, and J. Brabandt, Intl. J. Hydrogen Energy , 44 (35), 19089-19101, 2019. Hartvigsen, S. Elangovan, J. Elwell, and D. Larsen, ECS Trans. , 78 (1), 2953-2963, 2017. Figure 1