Investigation of Mars In-Situ Propellant Production

Reddig, Mike; MacKnight, Allen

doi:10.4271/972496

Cited by 2 publications

(2 citation statements)

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“…Their findings were significantly detailed from the standpoint of mission design. Later, in 1997, Reddig and MacKnight devised an integrated system that was capable of producing 0.7 kg/day of liquid methane from atmospheric carbon dioxide via a ruthenium-catalyzed Sabatier reaction (Reddig and MacKnight, 1997). They validated their methodology with a thermodynamic analysis of the ISPP system using black-box process modeling software.…”

Section: Introductionmentioning

confidence: 99%

Thermodynamic Modeling of In-Situ Rocket Propellant Fabrication on Mars

et al. 2022

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Section: Introductionmentioning

confidence: 99%

Thermodynamic Modeling of In-Situ Rocket Propellant Fabrication on Mars

et al. 2022

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“…Numerous studies have supported the use of in situ resources to reduce mission mass, cost, and risk for both robotic and human exploration, as well as to enhance, extend, or enable science and exploration objectives (Kaplan, 1996;Connolly and Zubrin, 1996;Zubrin et al 1997;Reddig and MacKnight, 1997;Green et al 1999;Sridhar et al 2000Sridhar et al , 2004. Previous studies have shown that producing propellants from Mars' atmospheric CO 2 and hydrogen brought from Earth can reduce initial mass launched by 20 to 45%, as compared to carrying all of the propellant for a round-trip mission to Mars (Sanders et al 2001).…”

Section: Introductionmentioning

confidence: 99%

Development of a Microchannel In Situ Propellant Production System

Brooks

Rassat²,

Hu³

et al. 2006

AIP Conference Proceedings

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This document was printed on recycled paper. PNNL-15456 Development of a MicrochannelIn Situ Propellant Production System Executive SummaryAn in situ propellant production plant (ISPP) on future Mars robotic missions can produce oxygen (O 2 ) and methane (CH 4 ) that can be used for propellant for the return voyage. By producing propellants from Mars' atmospheric carbon dioxide (CO 2 ) and hydrogen (H 2 ) brought from Earth, the initial mass launched in low Earth orbit can be reduced by 20 to 45%, as compared to carrying all of the propellant for a round-trip mission to Mars' surface from Earth. Furthermore, by utilizing ISPP, both robotic and manned missions to Mars can be enhanced, enabled, and extended. The propellant generated can provide fuel for hoppers and rovers for increased mobility on the surface, allow additional propellant to be created to increase the return trip payload, and provide oxygen for longer mission stays. With a durable heat source, this ISPP could also use in situ sources of hydrogen to provide a sustainable propellant supply.Pacific Northwest National Laboratory used microchannel architecture to develop a Mars-based In Situ Propellant Production (ISPP) system. This three-year research and development effort focused on process intensification and system miniaturization of two primary subsystems: a thermochemical compressor and catalytic reactors. Both of these systems were designed based on a robotic direct return mission scenario, but can be scaled up to human flight missions by simply numbering up the microchannel devices. A microchannel condenser/phase separator was developed under another NASA project. The results of this device are provided here to offer insight on performance of another necessary system component.The thermochemical collection and compression of CO 2 was developed using absorption and adsorption. Both membrane and microwicking absorbers were evaluated using 100-and 240-µm microchannels. CO 2 was absorbed from a 20%-CO 2 :80%-N 2 mixture into either a diethanolamine/water (DEA) or a DEA/PEG solution. Improved mass transfer was observed for the thinner films. Overall mass transfer coefficients were as much as 2.6 times greater than a conventional packed column for the thinnest microwick and about 7.1 times greater for the membrane system. A multichannel adsorption system was designed to meet the full-scale CO 2 collection requirements using temperature swing adsorption. Each stage is designed to achieve a 10x compression of CO 2 . A compression ratio to collect Martian atmospheric CO 2 at ~0.8 kPa and compress it to at least 100 kPa can be achieved with two adsorption stages in series. A compressor stage incorporates eight thermally coupled adsorption cells at various stages in the adsorption/desorption cycle to maximize the recuperation of thermal energy and provide a nearly continuous flow of CO 2 to the downstream reactors. Experimental work was performed in a single channel adsorber to validate this process. A temperature cycle between 12 and 77°C could be achie...

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Investigation of Mars In-Situ Propellant Production

Cited by 2 publications

References 12 publications

Thermodynamic Modeling of In-Situ Rocket Propellant Fabrication on Mars

Thermodynamic Modeling of In-Situ Rocket Propellant Fabrication on Mars

Development of a Microchannel In Situ Propellant Production System

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