In-Situ Resource Utilization: Methane Fuel Production

Metadata Updated: March 22, 2019

Sabatier reactors are being matured to produce methane from CO2 and hydrogen.[HTML_REMOVED] The hydrogen is derived from the electrolysis of soil-derived water, and the CO2 is derived from the Mars atmosphere.[HTML_REMOVED] A Sabatier system has been in use on the International Space Station (ISS) for some years so there is a high level of confidence in the technology, but In Situ Resource Utilization (ISRU) methane production requirements are much larger than the current ISS reactors. These reactors are exothermic catalyst-based systems that require thermal and flow management and post-reactor gas separation.[HTML_REMOVED] The ISRU Technology project is working challenges related to scaling up the reactor size, proper start-up and shutdown sequences, and the health and lifetime of the catalyst.Methane Fuel Production is part of the AES In-Situ Resource Utilization (ISRU) Technology Project which is developing the component, subsystem, and system technology to enable production of mission consumables from regolith and atmospheric resources at a variety of destinations for future human exploration missions.[HTML_REMOVED]The overall goals of the ISRU Technology project[HTML_REMOVED]are to achieve system-level TRL 6 to support future flight demonstration missions[HTML_REMOVED]and provide exploration architecture teams with validated, high-fidelity answers for mass, power, and volume of ISRU systems.The project[HTML_REMOVED]s initial focus is on critical technology gap closure[HTML_REMOVED]and component development in a relevant environment (TRL 5) for Resource Acquisition (excavation, drilling, atmosphere collection, and preparation/beneficiation before processing) and Resource Processing [HTML_REMOVED] Consumable Production (extraction and processing of resources into products with immediate use as propellants, life support gases, fuel cell reactants, and feedstock for construction and manufacturing). [HTML_REMOVED]The interim project goal is to complete ISRU subsystem[HTML_REMOVED]tests in a relevant environment to advance the[HTML_REMOVED]subsystem to TRL[HTML_REMOVED]6. [HTML_REMOVED]The project end goals are to perform end-to-end ISRU system tests in a relevant environment (system TRL 6)[HTML_REMOVED]and integrated ISRU-exploration elements demonstrations in a relevant environment.ISRU is a disruptive capability that enables more affordable exploration than today[HTML_REMOVED]s paradigm where all supplies are brought from Earth, and allows more sustainable architectures to be developed.[HTML_REMOVED] The availability of ISRU technologies can radically change the mission architecture[HTML_REMOVED]and be the sizing design driver for other complex systems already in development. For example, the current Mars architecture assumes ISRU production of up to 30 metric tons of propellant on the Mars surface in order to reduce the ascent vehicle landed mass by 75 percent and reduce Earth launch needs by at least 300 metric tons. If a decision was made to use storable propellants for the Mars ascent vehicle instead of ISRU-producible oxygen and methane, many other drastic changes to the architecture could be required, such as lander and ascent vehicle size, number of landers needed, surface operations for ascent vehicle fueling, and Mars rendezvous orbit.[HTML_REMOVED]Other surface systems might become more complex or heavier if they are not designed to take full advantage of ISRU technologies. Examples include a more complex closed-loop life support system if resupply with ISRU water cannot be assumed, or a heavy, built-in habitat radiation shield if a water- or regolith-based shield cannot be added after habitat delivery to the surface.Other system designers may also make decisions that reduce the benefit of incorporating ISRU into the mission, resulting in a larger or more inefficient ISRU system. For example, a non-continuous power source such as solar power would increase the required production rate and peak power of an ISRU plant, thus increasing its size and complexity due to hundreds of start-stop cycles.[HTML_REMOVED] However, a continuous power source, such as nuclear or solar power with storage, would allow an ISRU plant to operate continuously, thus minimizing its size, complexity, and power draw. These are only a few examples of how the inclusion of ISRU has ripple effects across many other exploration elements.ISRU is also a new capability that has never before been demonstrated in space or on another extraterrestrial body.[HTML_REMOVED] Every other exploration system or element, such as power, propulsion, habitats, landers, life support, rovers, etc., have some form of flight heritage, although almost all still need technology development to achieve the objectives of future missions. This is another critical reason why ISRU technology development, leading to a flight demonstration mission, needs to be started now, so that flight demonstration results can be obtained early enough to ensure that lessons learned can be incorporated into the final design.

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Metadata Created Date August 1, 2018
Metadata Updated Date March 22, 2019

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Harvested from NASA Data.json

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Resource Type Dataset
Metadata Created Date August 1, 2018
Metadata Updated Date March 22, 2019
Publisher Space Technology Mission Directorate
Unique Identifier TECHPORT_93847
Maintainer
TECHPORT SUPPORT
Maintainer Email
Public Access Level public
Bureau Code 026:00
Metadata Context https://project-open-data.cio.gov/v1.1/schema/catalog.jsonld
Metadata Catalog ID https://data.nasa.gov/data.json
Schema Version https://project-open-data.cio.gov/v1.1/schema
Catalog Describedby https://project-open-data.cio.gov/v1.1/schema/catalog.json
Datagov Dedupe Retained 20190322035503
Harvest Object Id 86a910ae-f40e-4e2f-b7cb-3c610af8dcb0
Harvest Source Id 39e4ad2a-47ca-4507-8258-852babd0fd99
Harvest Source Title NASA Data.json
Data First Published 2020-09-01
Homepage URL https://techport.nasa.gov/view/93847
License http://www.usa.gov/publicdomain/label/1.0/
Data Last Modified 2018-07-19
Program Code 026:027
Source Datajson Identifier True
Source Hash 4765183de358e5cd792f573384d02f8c25697124
Source Schema Version 1.1

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