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WATER EXTRACTION FROM REGOLITH
PRESENTER: LARA ORYSHCHYN 1
NASA’S JOURNEY TO MARS
GOAL: LIVE ON MARS & RETURN TO EARTH SAFELY
– Sustain Life: Oxygen, Water, Food, Shelter…
– Propellant: Oxygen, Methane
OPTIONS: BRING OR UTILIZE MARTIAN RESOURCES
– Atmosphere: CO2, N2, Ar, O2, CO… H2O (~210ppm)
– Regolith: The uppermost layer of the surface
2
HESTIA ARCHITECTURE
3
REGENERATIVE
GAS DRYER
REGENERATIVE
GAS DRYER
IN-SITU RESOURCE UTILIZATION (ISRU)
LIQUEFACTION
· LOCATION: MAV VS. SEPARATE
· TRANSFER PUMP
Mars
Soil
MARS
ATM
REGENERATIVE
DE-IONIZER
ELECTROLYZER
· ANODE VS. CATHODE
· HIGH VS. LOW PRESSURE
· OPERATING
TEMPERATURE
· ECLSS COMPATIBILITY
· SIMPLIFIED BALANCE OF PLANT
WATER ELECTROLYSIS
POWER
WET
O2
WET
H2
CLEAN
H2O
HEAT
DIRTY
H2O GAS
CLEAN
H2O LIQ.
WATER CLEANUP
· VAPOR VS. LIQUID PHASE
· ECLSS COMPATIBILITY
DIRTY
H2O LIQ.
CONDENSER
REGENERATIVE
CLEANER
VS.
DIRTY
H2O GAS
CLEAN
H2O GAS
CLEAN
H2O LIQ.
REGENERATIVE
CLEANER
CONDENSER
SOIL HOPPER
+ SIFTING
SOIL
FILTRATION
· ON ROVER VS. STATIONARY
SOIL HEATING
· DIRECT
· HOT SWEEP GAS
· MICROWAVE
· SCAVENGED
SOIL HARVEST /
TRANSPORT
DIRTY H2O
SPENT SOIL
REMOVAL
POWER
HEAT
SOIL PROCESSING
WET
SOIL
DIRTY
H2O
SPENT
SOIL
HOT, WET
SOIL
SABATIER
REACTOR
POWER
CO2
WET CH4
H2O
STARTUP HEAT
SABATIER
H2
SCAVENGED CO2
ALL-COMPOSITE
STRUCTURAL
TANKS
CRYO-FLUID
MANAGEMENT
ADVANCED
INSULATION
LIQUEFACTION
PUMP
O2
GAS
O2
GAS
O2
LIQ
O2
GAS
O2
LIQ
POWER
HEAT
ALL-COMPOSITE
STRUCTURAL
TANKS
CRYO-FLUID
MANAGEMENT
ADVANCED
INSULATION
LIQUEFACTION
PUMP
CH4
GAS
CH4
GAS
CH4
LIQ
CH4
GAS
CH4
LIQ
POWER
HEAT
CO
2
A
CQUISITION
CO2
CO
O2
POWER
STARTUP HEAT
SOLID-OXIDE
ELECTROLYZER (SOE)
CO2
SOLID OXIDE
ELECTROLYZER
COMMODITIES
PALLET
LOX
LCH4
H2O
CO2
To Ascent
Vehicle
To Hab
PROCESSING REGOLITH FOR WATER
4
EXCAVATION
TRANSPORTATION
WATER
EXTRACTION
WATER
PROCESSING
MARTIAN REGOLITH
BULK DENSITY: 1200-1600 KG/M3 [BARLOW, 95]
WATER CONTENT: ~1-10%
- Viking Landers: 1-2% [Anderson et al. 1979]
- Phoenix Lander: ~2% [Smith et al. 2009]
- MSL* Curiosity: ~2-5%[Leshin et al. 2013, Mitrofanov et al, 2014]
- Mars Express Orbiter: >10% [Milliken and Mustard 2007a,b…]
5
'Marias Pass,' Contact Zone of Two Martian Rock Units
Northward View Along West Rim of Endeavour
Photos:
Courtesy
of
NASA
[USGS RMRS-GTR-74,104]
*MSL: Mars Science Laboratory
DIG DEPTH BASED ON WATER CONTENT
AMERICAN FOOTBALL FIELD
HOW MUCH REGOLITH?
SUGGESTED PER DRA* 5.0 [AND SUBSEQUENT PUBLICATIONS]
– Duration: 510 days (480 days contingency)
– Total Oxygen Production: 25,000 kg
• Life Support: ~2,000 kg
• Propellant: ~23,000 kg
ASSUMPTIONS
– Operating Time: 24 hours/day
– Propellant (O2/CH4) Mixture Ratio: 4.0
– Atmospheric Processing with a Sabatier
→ Produces Half the Water
DERIVED RATES
– O2 Rate: 2.17 kg/hr (52.1 kg/day)
– H2O Total Rate: 2.44 kg/hr (58.6 kg/day)
– H2O Regolith Rate: 1.22 kg/hr (58.6 kg/day)
6
1%
2%
3%
15%
49 m (160’)
Not to Scale
*DRA: Design Reference Architecture
WATER EXTRACTION SYSTEM
AKA: SOIL PROCESSING MODULE (SPM)
HISTORY
– OPTIMA* (2007/2008)
• Lunar Regolith Hydrogen Reduction
• JSC-1A Simulant (10 kg)
• 1000 Metric Tons of O2/year
– HESTIA (2015/2016)
• Water Extraction of Martian Regolith
• JSC-Mars-1A Simulant (6 kg)
• Goal: 25,000 kg of O/~500 days
VERTICALLY AGITATED DRYER
– Nickname: Sandman
– Capacity:10,400 cm3 (630 in3)
7
*OPTIMA: Outpost Precursor Testbed for ISRU and Modular Architecture
FLUID
SYSTEM
SANDMAN
WATER EXTRACTION SYSTEM
8
58”
24”
WATER EXTRACTION SYSTEM
9
VALVES
FLUID
SYSTEM DRYER
HESTIA SPM TESTING
OBJECTIVES
– Determine water evolution rate using JSC-Mars-1A Simulant
– Evaluate the purity/contaminants of the water produced
– Identify upgrades/changes to the water extraction system
– Identify similarities/differences between Earth/Mars
TEST CONDITIONS
– Simulant Quantity: 6 kg
– Operating Pressure: <50 psig
– Operating Temperature: <500oC
– Sweep Gas: N2 or CO2
10
HESTIA SPM TESTING
11
Line
Freeze
WATER COLLECTOR
On Average: 19% Water by
Weight, Most Evolves within
2-3 after Heater Turned On
WHAT DID WE LEARN?
DRYER SHAPE MATTERS
– Current Design: Flat Bottom
– Future Designs: Should be Conical
REGOLITH EGRESS TUBE SIZE MATTERS
– Current Design: 1-1/4” OD Tube
– Future Designs: Larger ID
HEATER DESIGN NEEDS TO BE ROBUST
– Current Design: SiC Inside of a Heater Well
– Future Designs: Integrate into Vessel
PARTICULATE FILTRATION IS CHALLENGING
– Current Design: 5 micron filter inside Sandman
– Addition: Downstream Borosilicate Glass Filter
– Future Designs: Capture Particulate inside the Vessel if Possible
12
THE NEXT STEPS…
IMPROVE SIMULANT
– JSC-Mars-1A has too much Water: 19% vs. 3-9% expected on Mars
– JSC-Mars-1A does not have Water bound in Hydrated Salts as expected on Mars
DEVELOP MORE FLIGHT FORWARD DESIGN
– Simplify Fluid System
– Improve Condensing System
– Improve Dryer Design
• Incorporate Vacuum Compatible Components
• Improve Particulate Filtration
– Investigate Continuous Mode vs. Batch Mode
– Test Under Mars Conditions
INTEGRATE WITH OTHER ISRU HARDWARE
– Water Cleanup
– Electrolysis
– Regolith Feed/Removal System
13
REFERENCES
• ANDERSON ET AL,1979
• AUDOUARD ET AL. 2014 JGR
• BARLOW, NADINE G. MARS: AN INTRODUCTION TO ITS INTERIOR, SURFACE AND ATMOSPHERE. CAMBRIDGE, UK:
CAMBRIDGE UNIVERSITY PRESS, 2008.
• DRAKE, B.G., “HUMAN EXPLORATION OF MARS DESIGN REFERENCE ARCHITECTURE 5.0, EXECUTIVE SUMMARY,”
FEBRUARY 2009 (AVAILABLE FROM (AVAILABLE FROM
HTTP://NTRS.NASA.GOV/ARCHIVE/NASA/CASI.NTRS.NASA.GOV/20090012109.PDF).
• DRAKE, B.G. (EDITOR), “HUMAN EXPLORATION OF MARS DESIGN REFERENCE ARCHITECTURE 5.0,” NASA-SP-
2009-566, JULY 2009
• SMITH ET AL 2009
• LESHIN ET AL, 2013
• MITROFNOV ET AL, 2014
• MILLIKEN AND MUSTARD ET AL, 2007A,B
• UNITED STATES DEPARTMENT OF AGRICULTURE, SAMPLING SURFACE AND SUBSURFACE PARTICLE SIZE
DISTRIBUTIONS IN WADABLE GRAVEL- AND COBBLE-BED STREAMS FOR ANALYSES IN SEDIMENT TRANSPORT,
HYDRAULICS, AND STREAMBED MONITORING (USDA PUBLICATION RMRS-GTR-74). 2001
• SANDERS, G. B., “IN-SITU RESOURCE UTILIZATION ON MARS – UPDATE FROM DRA 5.0 STUDY,” AIAA 2010-799,
JANUARY 2010.
14
PRESENTATION NOTES
FROM BRIAN BANKER
15
THIS IS A TEST OF THE TEMPLATE SYSTEM
FORMAT
– Use this slide deck for template
– Time Limit 25 min:
• 15 min talk
• 10 min questions
– Picture Heavy
– Upload Files here by COB Friday, 29th
• https://oasis.jsc.nasa.gov/projects/HESTIA/EP/AIAA%20H
ouston%20Tech%20Symposium/Forms/AllItems.aspx
16
FLOW
WHERE WE FIT INTO THE ARCHITECTURE
BACKGROUND OF TECHNOLOGY
– How long have we been working on it
– Why it (the technology)?
WHERE WE ARE NOW
– What we’re doing at JSC
WHAT’S NEXT FOR THE TECHNOLOGY
17
TITLE
ADD HERE
– Add here
• Add here
– Add here
• Add here
ADD HERE
– Add here
• Add here
– Add here
• Add here
18

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aiaawater_production.pptx

  • 1. WATER EXTRACTION FROM REGOLITH PRESENTER: LARA ORYSHCHYN 1
  • 2. NASA’S JOURNEY TO MARS GOAL: LIVE ON MARS & RETURN TO EARTH SAFELY – Sustain Life: Oxygen, Water, Food, Shelter… – Propellant: Oxygen, Methane OPTIONS: BRING OR UTILIZE MARTIAN RESOURCES – Atmosphere: CO2, N2, Ar, O2, CO… H2O (~210ppm) – Regolith: The uppermost layer of the surface 2
  • 3. HESTIA ARCHITECTURE 3 REGENERATIVE GAS DRYER REGENERATIVE GAS DRYER IN-SITU RESOURCE UTILIZATION (ISRU) LIQUEFACTION · LOCATION: MAV VS. SEPARATE · TRANSFER PUMP Mars Soil MARS ATM REGENERATIVE DE-IONIZER ELECTROLYZER · ANODE VS. CATHODE · HIGH VS. LOW PRESSURE · OPERATING TEMPERATURE · ECLSS COMPATIBILITY · SIMPLIFIED BALANCE OF PLANT WATER ELECTROLYSIS POWER WET O2 WET H2 CLEAN H2O HEAT DIRTY H2O GAS CLEAN H2O LIQ. WATER CLEANUP · VAPOR VS. LIQUID PHASE · ECLSS COMPATIBILITY DIRTY H2O LIQ. CONDENSER REGENERATIVE CLEANER VS. DIRTY H2O GAS CLEAN H2O GAS CLEAN H2O LIQ. REGENERATIVE CLEANER CONDENSER SOIL HOPPER + SIFTING SOIL FILTRATION · ON ROVER VS. STATIONARY SOIL HEATING · DIRECT · HOT SWEEP GAS · MICROWAVE · SCAVENGED SOIL HARVEST / TRANSPORT DIRTY H2O SPENT SOIL REMOVAL POWER HEAT SOIL PROCESSING WET SOIL DIRTY H2O SPENT SOIL HOT, WET SOIL SABATIER REACTOR POWER CO2 WET CH4 H2O STARTUP HEAT SABATIER H2 SCAVENGED CO2 ALL-COMPOSITE STRUCTURAL TANKS CRYO-FLUID MANAGEMENT ADVANCED INSULATION LIQUEFACTION PUMP O2 GAS O2 GAS O2 LIQ O2 GAS O2 LIQ POWER HEAT ALL-COMPOSITE STRUCTURAL TANKS CRYO-FLUID MANAGEMENT ADVANCED INSULATION LIQUEFACTION PUMP CH4 GAS CH4 GAS CH4 LIQ CH4 GAS CH4 LIQ POWER HEAT CO 2 A CQUISITION CO2 CO O2 POWER STARTUP HEAT SOLID-OXIDE ELECTROLYZER (SOE) CO2 SOLID OXIDE ELECTROLYZER COMMODITIES PALLET LOX LCH4 H2O CO2 To Ascent Vehicle To Hab
  • 4. PROCESSING REGOLITH FOR WATER 4 EXCAVATION TRANSPORTATION WATER EXTRACTION WATER PROCESSING
  • 5. MARTIAN REGOLITH BULK DENSITY: 1200-1600 KG/M3 [BARLOW, 95] WATER CONTENT: ~1-10% - Viking Landers: 1-2% [Anderson et al. 1979] - Phoenix Lander: ~2% [Smith et al. 2009] - MSL* Curiosity: ~2-5%[Leshin et al. 2013, Mitrofanov et al, 2014] - Mars Express Orbiter: >10% [Milliken and Mustard 2007a,b…] 5 'Marias Pass,' Contact Zone of Two Martian Rock Units Northward View Along West Rim of Endeavour Photos: Courtesy of NASA [USGS RMRS-GTR-74,104] *MSL: Mars Science Laboratory
  • 6. DIG DEPTH BASED ON WATER CONTENT AMERICAN FOOTBALL FIELD HOW MUCH REGOLITH? SUGGESTED PER DRA* 5.0 [AND SUBSEQUENT PUBLICATIONS] – Duration: 510 days (480 days contingency) – Total Oxygen Production: 25,000 kg • Life Support: ~2,000 kg • Propellant: ~23,000 kg ASSUMPTIONS – Operating Time: 24 hours/day – Propellant (O2/CH4) Mixture Ratio: 4.0 – Atmospheric Processing with a Sabatier → Produces Half the Water DERIVED RATES – O2 Rate: 2.17 kg/hr (52.1 kg/day) – H2O Total Rate: 2.44 kg/hr (58.6 kg/day) – H2O Regolith Rate: 1.22 kg/hr (58.6 kg/day) 6 1% 2% 3% 15% 49 m (160’) Not to Scale *DRA: Design Reference Architecture
  • 7. WATER EXTRACTION SYSTEM AKA: SOIL PROCESSING MODULE (SPM) HISTORY – OPTIMA* (2007/2008) • Lunar Regolith Hydrogen Reduction • JSC-1A Simulant (10 kg) • 1000 Metric Tons of O2/year – HESTIA (2015/2016) • Water Extraction of Martian Regolith • JSC-Mars-1A Simulant (6 kg) • Goal: 25,000 kg of O/~500 days VERTICALLY AGITATED DRYER – Nickname: Sandman – Capacity:10,400 cm3 (630 in3) 7 *OPTIMA: Outpost Precursor Testbed for ISRU and Modular Architecture FLUID SYSTEM SANDMAN
  • 10. HESTIA SPM TESTING OBJECTIVES – Determine water evolution rate using JSC-Mars-1A Simulant – Evaluate the purity/contaminants of the water produced – Identify upgrades/changes to the water extraction system – Identify similarities/differences between Earth/Mars TEST CONDITIONS – Simulant Quantity: 6 kg – Operating Pressure: <50 psig – Operating Temperature: <500oC – Sweep Gas: N2 or CO2 10
  • 11. HESTIA SPM TESTING 11 Line Freeze WATER COLLECTOR On Average: 19% Water by Weight, Most Evolves within 2-3 after Heater Turned On
  • 12. WHAT DID WE LEARN? DRYER SHAPE MATTERS – Current Design: Flat Bottom – Future Designs: Should be Conical REGOLITH EGRESS TUBE SIZE MATTERS – Current Design: 1-1/4” OD Tube – Future Designs: Larger ID HEATER DESIGN NEEDS TO BE ROBUST – Current Design: SiC Inside of a Heater Well – Future Designs: Integrate into Vessel PARTICULATE FILTRATION IS CHALLENGING – Current Design: 5 micron filter inside Sandman – Addition: Downstream Borosilicate Glass Filter – Future Designs: Capture Particulate inside the Vessel if Possible 12
  • 13. THE NEXT STEPS… IMPROVE SIMULANT – JSC-Mars-1A has too much Water: 19% vs. 3-9% expected on Mars – JSC-Mars-1A does not have Water bound in Hydrated Salts as expected on Mars DEVELOP MORE FLIGHT FORWARD DESIGN – Simplify Fluid System – Improve Condensing System – Improve Dryer Design • Incorporate Vacuum Compatible Components • Improve Particulate Filtration – Investigate Continuous Mode vs. Batch Mode – Test Under Mars Conditions INTEGRATE WITH OTHER ISRU HARDWARE – Water Cleanup – Electrolysis – Regolith Feed/Removal System 13
  • 14. REFERENCES • ANDERSON ET AL,1979 • AUDOUARD ET AL. 2014 JGR • BARLOW, NADINE G. MARS: AN INTRODUCTION TO ITS INTERIOR, SURFACE AND ATMOSPHERE. CAMBRIDGE, UK: CAMBRIDGE UNIVERSITY PRESS, 2008. • DRAKE, B.G., “HUMAN EXPLORATION OF MARS DESIGN REFERENCE ARCHITECTURE 5.0, EXECUTIVE SUMMARY,” FEBRUARY 2009 (AVAILABLE FROM (AVAILABLE FROM HTTP://NTRS.NASA.GOV/ARCHIVE/NASA/CASI.NTRS.NASA.GOV/20090012109.PDF). • DRAKE, B.G. (EDITOR), “HUMAN EXPLORATION OF MARS DESIGN REFERENCE ARCHITECTURE 5.0,” NASA-SP- 2009-566, JULY 2009 • SMITH ET AL 2009 • LESHIN ET AL, 2013 • MITROFNOV ET AL, 2014 • MILLIKEN AND MUSTARD ET AL, 2007A,B • UNITED STATES DEPARTMENT OF AGRICULTURE, SAMPLING SURFACE AND SUBSURFACE PARTICLE SIZE DISTRIBUTIONS IN WADABLE GRAVEL- AND COBBLE-BED STREAMS FOR ANALYSES IN SEDIMENT TRANSPORT, HYDRAULICS, AND STREAMBED MONITORING (USDA PUBLICATION RMRS-GTR-74). 2001 • SANDERS, G. B., “IN-SITU RESOURCE UTILIZATION ON MARS – UPDATE FROM DRA 5.0 STUDY,” AIAA 2010-799, JANUARY 2010. 14
  • 16. THIS IS A TEST OF THE TEMPLATE SYSTEM FORMAT – Use this slide deck for template – Time Limit 25 min: • 15 min talk • 10 min questions – Picture Heavy – Upload Files here by COB Friday, 29th • https://oasis.jsc.nasa.gov/projects/HESTIA/EP/AIAA%20H ouston%20Tech%20Symposium/Forms/AllItems.aspx 16
  • 17. FLOW WHERE WE FIT INTO THE ARCHITECTURE BACKGROUND OF TECHNOLOGY – How long have we been working on it – Why it (the technology)? WHERE WE ARE NOW – What we’re doing at JSC WHAT’S NEXT FOR THE TECHNOLOGY 17
  • 18. TITLE ADD HERE – Add here • Add here – Add here • Add here ADD HERE – Add here • Add here – Add here • Add here 18

Editor's Notes

  1. Atmospher:: Major : Carbon Dioxide (CO2) - 95.32% ; Nitrogen (N2) - 2.7% ; Argon (Ar) - 1.6%; Oxygen (O2) - 0.13%; Carbon Monoxide (CO) - 0.08% Minor (ppm): Water (H2O) - 210; Nitrogen Oxide (NO) - 100; Neon (Ne) - 2.5; Hydrogen-Deuterium-Oxygen (HDO) - 0.85; Krypton (Kr) - 0.3; Xenon (Xe) - 0.08