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At least 577 records · Page 32
All sourcesNASA NTRSDOE OSTI
NASA NTRSDate not supplied

Modeling Electrolytic O2 Recovery from Metabolic CO2 for Advanced Closed Loop Life Support Systems in Extraterrestrial Human Missions

The International Space Station (ISS) is currently equipped with a complex, heavy, and power consuming system that recovers approximately 50% of O2 from metabolic CO2. Future long duration human missions to the Moon and Mars will necessitate a sustainable and highly efficient metabolic oxygen recovery system capable of yielding a minimum of 75% O2 recovery. A Macrofluidic Electrochemical Reactor (MFECR) technology development effort is currently underway at NASA Marshall Space Flight Center (MSFC) to significantly increase current metabolic O2 recovery efficiency, expand mission sustainability, and reduce complexity of the system. The novel design combines CO2 conversion to O2 along with C2H4 as byproduct and water electrolysis (currently conducted in two separate units) into a single compact unit that runs at standard conditions and is theoretically capable of generating O2 with a theoretical maximum metabolic CO2 conversion of 73% while consuming less than metabolic water. This paper presents a comprehensive multi-physic 3D model developed at MSFC on CO2 conversion to O2 and C2H4 at standard conditions via MFECR. The 3D spatial domain of the model is a replica of the actual MFECR’s 3D drawing generated for the MFECR fabrication and operated to recover O2 from CO2 yielding C2H4 as byproduct. Electrochemical (EC) physics that includes EC multicomponent reaction mechanisms, mass transport, and electrical current density distributions is coupled in the model with all the other physics phenomena involved in the MFECR’s process, such as two-phase flow, free and porous fluid regimes, multicomponent mass transfer, heat transfer, and DC electrical current generation along with Joule heating effect. The EC reaction sections of the MFECR consists of two porous gas diffusion electrodes (GDE) and an electrolyte serpentine channel sandwiched in the middle. The CO2 feeds the cathode serpentine channel and part of the O2 product is fed back to the anode serpentine chamber. An alkaline solution feeds the electrolyte serpentine chamber wetting the GDEs of both, the anode and cathode allowing the OH- ionic transport between them. The EC reactions in the cathode’s GDE yield C2H4 from CO2 and H2 from water while the EC reaction in the anode’s GDE yields O2. The authors will present in this paper the validation of the model using experimental data and the utilization of the validated model in building a reliable simulator that will not only assist the authors on the MFECR design but also the optimization of its operation in the ISS and future spatial human missions.

Jesus A Dominguez↗
NASA NTRSDate not supplied

Off Earth Landing and Launch Pad Construction – A Critical Technology for Establishing a Long-Term Presence on Extraterrestrial Surfaces

Space Policy Directive 1 has refocused the National Aeronautics and Space Administration (NASA) to lead the return of humans to the Moon for long-term exploration and utilization. A long-term presence on the moon will require numerous lunar landings and launches to build up surface assets, rotate crew, and deliver resources to/from the moon. Interactions between landing/launch plumes and the unprepared surface cause regolith to be eroded and ejected at high velocities from beneath the vehicle. The associated ejecta elevates mission risks by obscuring sensors and human vision during landing; cratering/modifying the surface that the vehicle will land upon; and subjecting the vehicle, surrounding assets, and potentially orbital assets to impacts from high velocity dust particles. A method to mitigate risks stemming from landing/launch plume ejecta is to construct reusable landing/launch pads. A landing/launch pad can provide a known landing/launch surface, minimize ejecta, protect assets from liberated particles, and provide protection in case of a landing/launch anomaly. This presentation will summarize previous work towards construction of off-Earth landing/launch pads and identify key technology gaps. Additionally, this presentation establishes metrics for comparison of pad construction technologies and trades current approaches. The overall objective of this paper is to baseline the state of the art of off-Earth landing/launch pad construction technologies and serve as the starting point for further technical development.

Landing & Launch Pad↗
NASA NTRS2021

Extraterrestrial Hydroxy Amino Acids in CM and CR Carbonaceous Chondrites

7 The abundances, distributions, and enantiomeric ratios of a family of three- and four- 8 9 10 carbon hydroxy amino acids (HAAs) were investigated in extracts of five CM and four 11 12 13 CR carbonaceous chondrites by gas chromatography-mass spectrometry (GC-MS) 14 15 16 analyses. Hydroxy amino acids were detected in both the acid hydrolysates of the hot 17 18 19 water extracts and the 6 M HCl extracts of all the CM and CR chondrites analyzed 20 21 22 here with total hot water and HCl extractable HAA concentrations ranging from 6.94 23 24 25 to 315 nmol per gram. The HAA analyses performed in this study revealed: 1) the 26 27 28 combined (hot water + HCl) extracts of CR2 chondrites contained greater abundances 29 30 31 of -HAAs than that of CM2 chondrites and 2) the combined extracts of CM and CR 32 33 34 chondrites contained roughly similar abundances of β- and γ-HAAs. Application of the 35 36 37 new GC-MS method developed here resulted in the first successful chromatographic 38 39 40 resolution of the enantiomers of an -dialkyl HAA, D,L--methylserine, in 41 42 43 carbonaceous chondrite extracts. Meteoritic -methylserine was found to be mostly 44 45 46 racemic within error and did not show L-enantiomeric excesses correlating with the 47 48 49 degree of aqueous alteration, a phenomenon observed in meteoritic isovaline, another 50 51 52 -dialkyl amino acid. The HAAs identified in CM and CR chondrite extracts could have 53 54 55 been produced during parent body alteration from the Strecker cyanohydrin reaction 56 57 58 (for -HAAs) and an ammonia-involved formose-like reaction (for β-, and γ-HAAs).

Amino acid(s), CM carbonaceous chondrite < Meteori↗
NASA NTRS2021

Extraterrestrial hydroxy amino acids in CM and CR carbonaceous chondrites

The abundances, distributions, and enantiomeric ratios of a family of three- and four-carbon hydroxy amino acids (HAAs) were investigated in extracts of five CM and four CR carbonaceous chondrites by gas chromatography-mass spectrometry analyses. HAAs were detected in both the acid hydrolysates of the hot water extracts and the 6 M HCl extracts of all the CM and CR chondrites analyzed here with total hot water and HCl extractable HAA concentrations ranging from 6.94 to 315 nmol/g. The HAA analyses performed in this study revealed: (1) the combined (hot water + HCl) extracts of CR2 chondrites contained greater abundances of α-HAAs than that of CM2 chondrites and (2) the combined extracts of CM and CR chondrites contained roughly similar abundances of β- and γ-HAAs. Application of the new GC-MS method developed here resulted in the first successful chromatographic resolution of the enantiomers of an α-dialkyl HAA, d,l-α-methylserine, in carbonaceous chondrite extracts. Meteoritic α-methylserine was found to be mostly racemic within error and did not show l-enantiomeric excesses correlating with the degree of aqueous alteration, a phenomenon observed in meteoritic isovaline, another α-dialkyl amino acid. The HAAs identified in CM and CR chondrite extracts could have been produced during parent body alteration from the Strecker cyanohydrin reaction (for α-HAAs) and an ammonia-involved formose-like reaction (for β-, and γ-HAAs).

Amino acid(s)↗
NASA NTRS2022

THE NASA SPLICE PROJECT’S TERRESTRIAL TESTING OF EXTRATERRESTRIAL PRECISION LANDING SYSTEMS

The Safe and Precise Landing—Integrated Capabilities Evolution (SPLICE) project continues a NASA legacy of advancing precision landing and hazard avoidance (PL&HA) capabilities. In order to rapidly and cost-effectively de-velop and demonstrate PL&HA systems, terrestrial and suborbital testing of these path-to-spaceflight technologies is commonly used. Creating test envi-ronments on Earth that are sufficiently similar to their intended spaceflight envi-ronment is challenging. This paper will cover the experiences of the SPLICE project across its terrestrial test campaigns in preparation for lunar demonstra-tion missions.

Samuel Pedrotty↗