Martian Liquid CO2 and Metabolic Heat Regenerated Temperature Swing Adsorption for Portable Life Support Systems

Iacomini, Christine; MacCallum, Taber; Morin, Tom; Straub-Lopez, Kathrine; Paul, Heather L.

doi:10.1063/1.2437527

Cited by 12 publications

(5 citation statements)

References 4 publications

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“…Extraction and compression of carbon dioxide gas are then realized by a sorption compressor 32,46,47 . It uses an adsorbent mircroporous material, that can trap vapour and gas molecules within its pores.…”

Section: Selective Compressionmentioning

confidence: 99%

Hybrid Rocket Propulsion and In-Situ Propellant Production for Future Mars Missions

Boiron

Cantwell

2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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This article shows that a combination of in-situ resource utilization and hybrid rocket propulsion represents a very competitive solution for future medium to large-scale missions to the red planet. A high performance liquid oxygen/paraffin medium-scale hybrid ascent vehicle, of which the oxidizer has been acquired through decomposition of carbon dioxide on the surface of Mars, is estimated to achieve more than 40% mass reduction in respect to the same vehicle brought from Earth, thus outperforming all conventional designs. All the technologies needed are detailed and the in-situ propellant production (ISPP) unit is precisely sized for two selected missions: Mars Sample Return (payload of 36 kg) and the medium-scale case (payload of 500 kg). The many advantages of this design (notably in simplicity, safety and size) over currently dominant in-situ liquid-powered concepts are discussed. The innovative idea described in this article supports renewed interest in hybrid rocket propulsion for space exploration and opens the way for newly ambitious robotic and manned missions to the planet Mars. NomenclatureISPP = in-situ propellant production EDL = entry, descent and landing MSR = Mars sample return MAV = Mars ascent vehicle LMO = low Mars orbit TRL = technology readiness level YSZ = yttrium-stabilized zirconia RTG = radioisotope thermoelectric generator RPS = radioisotope power system ASRG = advanced stirling radioisotope generator CO 2 = carbon dioxide O 2 = dioxygen CO = carbon monoxide LOX = liquid oxygen (cryogenic fluid) O/F = oxidizer to fuel ratio sol = martian day

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Section: Selective Compressionmentioning

confidence: 99%

Hybrid Rocket Propulsion and In-Situ Propellant Production for Future Mars Missions

Boiron

Cantwell

2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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“…Each bed is cycled between adsorb and desorb mode. The concept and its development history has been described previously in detail, 1,2,3,4 but is summarized briefly here as well. A schematic demonstrating how the MTSA can be employed in a PLSS is shown in Figure 1.…”

Section: Nomenclaturementioning

confidence: 99%

Simulated Lunar Testing of Metabolic heat regenerated Temperature Swing Adsorption

Padilla

Bower

Iacomini

et al. 2012

42nd International Conference on Environmental Systems

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Metabolic heat regenerated Temperature Swing Adsorption (MTSA) technology is being developed for thermal and carbon dioxide (CO 2 ) control for a Portable Life Support System (PLSS), as well as water recycling. An Engineering Development Unit (EDU) of the MTSA Subassembly (MTSAS) was designed and assembled for optimized Martian operations, but also meets requirements for lunar operations. For lunar operations the MTSA sorption cycle is driven via a vacuum swing between suit ventilation loop pressure and lunar vacuum. The focus of this effort was testing in a simulated lunar environment. This environment was simulated in Paragon's ECLSS Human-rating Facility (EHF) chamber. The objective of the testing was to evaluate the full cycle performance of the MTSAS EDU, and to assess CO 2 loading and pressure drop of the wash coated aluminum reticulated foam sorbent bed. Lunar environment testing proved out the feasibility of pure vacuum swing operation, making MTSA a technology that can be tested and used on the Moon prior to going to Mars. Testing demonstrated better than expected CO 2 loading on the sorbent and nearly replicates the equilibrium data from the sorbent manufacturer. This exceeded any of the previous sorbent loading tests performed by Paragon. Subsequently, the increased performance of the sorbent bed design indicates future designs will require less mass and volume than the current EDU rendering MTSA as very competitive for Martian PLSS applications. Nomenclature

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“…2) MTSA does not require consumables brought from Earth. The LCO 2 coolant can be made on Mars using the Martian atmosphere for relatively low infrastructure and energy costs [1]. This is a significant mission mass savings and reduction in risk.…”

Section: Introductionmentioning

confidence: 99%

“…Preliminary sizing has been performed for an adsorbent bed/heat exchanger assembly, the major component of a MTSA system [1]. Small feasibility experiments and modeling have been on-going to asses the design and performance of that assembly [2,3].…”

Section: Introductionmentioning

confidence: 99%

“…Small feasibility experiments and modeling have been on-going to asses the design and performance of that assembly [2,3]. Of a larger picture, a Martian LCO 2 plant architecture was presented to communicate the process of acquiring and storing the LCO 2 resource on Mars [1]. Evaluation of possible MTSA systems should begin to assess architecture decisions, operations and identify any challenges in MTSA implementation.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Testing, Modeling and System Impact of Metabolic Heat Regenerated Temperature Swing Adsorption

Iacomini¹,

Powers²,

Lewis³

et al. 2008

SAE Technical Paper Series

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Martian Liquid CO2 and Metabolic Heat Regenerated Temperature Swing Adsorption for Portable Life Support Systems

Cited by 12 publications

References 4 publications

Hybrid Rocket Propulsion and In-Situ Propellant Production for Future Mars Missions

Hybrid Rocket Propulsion and In-Situ Propellant Production for Future Mars Missions

Simulated Lunar Testing of Metabolic heat regenerated Temperature Swing Adsorption

Testing, Modeling and System Impact of Metabolic Heat Regenerated Temperature Swing Adsorption

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