aero 426 -500 fall 2014 lunar base design · • hub units to centralize movement, isolation...
TRANSCRIPT
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AERO – 426 -500
FALL 2014
LUNAR BASE DESIGN
Program Manager: Chase Lookofsky
Assistant Program Manager: Akshay Shankar
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Overview• Mission Statement
• Team Organization
• Base Siting and Location
• Consumables
• Return on Investment
• Biohazard
• Transportation
• Fail Safe Environment
Chase Lookofsky2
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Mission Statement
“The mission is to design permanent, self-sufficient, manned settlement on the moon that will provide a critical stepping stone for mankind’s ultimate destiny of
interplanetary colonization.”
Chase Lookofsky 3
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Team Organization
Chase Lookofsky
Project Manager
Chase Lookofsky
Base Siting and Layout
Renner Mead
Return On Investment
Alexander Ward
Biohazard Protection
Garrett Perez
Consumables
Matthew Henley
Transportation
Zack Zukowski
Fail Safe Environment
Hannah Fontenot
Assistant Project Manager
Akshay Shankar
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Base Siting
Layout
& Construction
Technical Group Leader: Renner Mead
Scott McQuien
Erik Hoffman
Steven Post
Luis Hernandez
Connor Cooper
Dominic Kelley
Mauricio Coen
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Overview• Logistics
– Location on moon
– Overall base layout
• Structural approach– General modular design
• Base elements– Living quarters
– Kitchen
– Medical
– Recreational
– Laboratories
– Storage
William Mead 6
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LOGISTICS
LOCATION ON MOON
OVERALL BASE LAYOUT
William Mead
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Logistics: Location On Moon
• North/South Pole
– Bottom of some craters never see sunlight
– High Possibility of solid H2O due to prolonged and
constant low temperatures
– North pole likely home to more water than South
pole
• Equator
– Few to no areas in constant shadow
– Low possibility of H2O due to fluctuating
temperatures throughout lunar day.
http://lunar.arc.nasa.gov/results/neures.htm
8Mauricio Coen
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Logistics: Location On Moon (2)
• North Pole
– Crater Basins
• Constant Shadow
– Crater Rims
• Constant Sunlight
– Max. surface variations 100K (300K for equator)
– Below surface temperatures 40-45K warmer and imperceptible fluctuation
– Gentle thermal stress fatigue cycle.
– Beneficial to long-term hardware
http://wattsupwiththat.com/2012/01/22/unified-theory-of-climate-
reply-to-comments/
9
http://diviner.ucla.edu/science.shtml
Mauricio Coen
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Logistics: Location On Moon (3)• Peary Crater
• North Pole
• 88.5°N, 33°E,
• Crater Diameter: 75 km.
• Leveled Basin
• Between 2 to 4 km deep
• Gradients <20%
7Mauricio Coen
http://lroc.sese.asu.edu/images
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Logistics: Location On Moon (4)
http://www.nature.com/nature/journal/v434/n7035/fig_tab/434842a_F1.html
10Mauricio Coen
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Base Layout
Scott McQuien 12
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Base Layout: Rationale
• Four person living modules
• Generalized labs
• Hub units to centralize movement, isolation outfitted (failsafe)
• Connection type: Enclosed pathways, safety airlocks at each end
– Each unit has at-least two entrance/exits
• Expansion capability streamlined
Scott McQuien 13
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Structural Approach
MODULE DESIGN
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Module Design: Characteristics
Standard Module Design
• All Structural Elements Based on Same General Platform
– Regolith Submerged, Inflatable Structures
– Inflatable Element Attached to Rigid Airlock and Systems Housing
– Standard Module Size: 50 m^
– Partitioned rooms
– Assisted Movement Airlock Corridors
Conner Cooper 15
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Module Design: Construction• Inflatable Structures
– Landed and deployed on Lunar Surface
Conner Cooper
Inflatable
AirlockAirlockInflated
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Module Design: Construction
• Autonomous Robots
– Deployed with Inflatables
– Contain Regolith Scoop and Regolith Sintering Device
Conner Cooper
Sintering Device
Regolith Scoop
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Module Design: Construction
• Robots pile up regolith around base, sinter into place
• ESA has proposed idea that is very similar to this
Conner Cooper
Inflatable
Airlock
Regolith
InflatablePiling Up Regolith
Sintering in Place
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Base Elements
HUB UNIT
LIVING QUARTERS
LABORATORIES
STORAGE
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Hub Unit
• 50 m2
• Home to:
– Kitchen
– Recreation
– Medical
Dominic Kelley
KITCHEN
RECREATION
MEDICAL
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Kitchen
• 15 m2
• General cooking area
• Pantry
• Eating area
Dominic Kelley 21
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Medical• 15m2
• Exercise Equipment
– Combat muscle atrophy
– Morale booster
• Stationary Bike
– Resistance Training
• COLBERT Treadmill
– Artificial gravity aerobic activity
• Bow flex
– Gravity independent system
Dominic Kelley 22
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Recreation• 20 m2
• Large TV
– Movie nights
• Foldable Ping Pong Table
• Darts
• Shenanigans
• Internet Access
– Access to wide variety of entertainment
• Wii
– Sports Simulation
• Kindle/E-Books
– Lighter/Smaller than books
Dominic Kelley 23
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Living Quarters: Characteristics
• 8 m2 per room
• 1 m hallways
• 4.5 inch interior wall thickness
• Based off standards from “home guides” http://homeguides.sfgate.com/instructions-building-interior-wall-24777.html
• 50cm exterior thickness
• Protection from radiation
Erik Hoffman 24
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Living Quarters: Layout
Erik Hoffman 25
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Laboratories: Characteristics
• LAB DESIGN
• 8 crew members = 100 square meters
• Combination of Open & Closed lab for usable open area and closed areas for special experiments needing a special environment.
• Almost all laboratory personnel require both laboratory & office space. Need to include both in design.
• Considering current technology needs, a good science area requires a minimum of 60 square ft per person. Due to the seriousness of experiments we will assume lab space for each person is 90 square ft.
• Source: http://www.flinnsci.com/teacher-resources/safety/general-laboratory-safety/overcrowding-in-the-science-laboratory/
Steven Post 26
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Laboratories: Layout
Steven Post 27
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12m2
12m2 12m2
12m2
Storage Characteristics
• Inflatable Structure
• 12 m2
– Based on Rising S Admiral Series - 20’X80’ “Doomsday” Bunker
• Airlock placement will allow grouping of storage area structures
Conner Cooper 28
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Storage: LayoutThree isolated storage sectors
– (1) 4 m2
– (2) 1.5 m2
Modular racking system
– Drawers: Consumables,
Temp control
– Shelves: Spare parts
– Bins: Raw materials
Three possible entrance/exits
Scott McQuien 29
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Consumables
Technical Group Leader: Matthew Henley
Sumit Pokhrel
Sean Brady
Benjamin Evart
Meredith Davis
Nathan Hughart
Kevin Lim
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Required Consumables• Required resupply of no more than 10,000 kilograms per year
• Food, Oxygen, and Water requirements for a crew of 8 are derived from Fall 2012 AERO 426 requirements for a crew of
12.
– Oxygen: 2454 kg/yr.
– Water: 8767 kg/yr.
– Food: 6234 kg/yr.
• 17,500 kg/yr. required in total. Depending solely on resupply is not feasible.
• In-house farming and oxygen/water recycling and in-situ resource utilization are necessary to meet resupply
requirement.
Matthew Henley 31
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Life Support: Water RecyclingBased on ISS Environmental Control and Life Support System (ECLSS):
• ISS Water Recovery System (WRS)
– Traditional water distillation requires gravity which is lacking in space. WRS uses
spinning drum to emulate gravity. Recycles urine, humidity, and greywater to
produce water that is potable by “the highest standards”
– Recovers about 70% of used water in practice
– Estimated to decrease necessary water resupply by 6,800 kg/yr. in water on ISS.
– Source: http://www.water-technology.net/projects/iss_water_recovery/
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Life Support: Oxygen Generation• Humans require minimum 15% oxygen content to survive
• Lunar base will use 78/22 ratio for percentages of Nitrogen to Oxygen at 1 atm.
• Oxygen Generation Assembly (OGA) uses electrolysis produced by WRS to produce oxygen
– Produces 2.3 to 9 kg/day of oxygen (continuous operation)
– 5.4 kg/day of oxygen (cyclic operation)
– Will use plants to supplement and sustain oxygen indefinitely
Combined with in-situ resource utilization, water and oxygen are projected to be a non-factor for resupply.
• Onboard system to monitor and control atmospheric conditions
Matthew Henley 33
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• Fire is very dangerous in space systems, as such, a fire
suppression system must be considered.
• Due to lower gravity on the moon, smoke detectors
should be placed within the ventilation system.
• Three Step Process used on the ISS can be applied to
the moon base:
– Turn off ventilation systems (air masks should be
worn for crew safety)
– Turn off power to the unit that has caught fire
– Use a Fire Extinguisher
• Fire Extinguishers and air masks should be placed in
every structure and be easily obtainable
Life Support: Fire Suppression
http://www.nasa.gov/images/content/57401main_040104_fir
e_prevention.jpg
Kevin lim 34
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Food• Food will need to be grown on-site or shipped in.
– Assuming water and oxygen remain non-factor for resupply, shipping is feasible option, but not ideal
• Alternative, use a greenhouse to grow food on-site.
• Ideal candidate: the prototype lunar greenhouse currently under research at University of Arizona Controlled
Environment Agriculture Center (CEAC)
• Or…
Matthew Henley 35
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Lunar Greenhouse• Grows plants hydroponically
• Carbon dioxide delivered from
astronauts
• Uses water from WRS and lunar ice
• Average consumption in testing:
• Power: 4.167 kW (100 kWh/day)
• CO2: 0.22 kg/day
• Water: 25.7 L/day
• Average production in testing:
• Water: 21.4 ± 1.9 L/day
• Biomass: 0.06 ± 0.01 kg/m2/day
• Measured labor demand:
• 35.9 min/day labor for operations
Meredith davis 36
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Lunar Greenhouse (2)• Sunlight is delivered to the plants via fiber optic cables
with a Fresnel-based solar concentrator (Pictured right)
• Pictured right in Fig 2.A is the old asterisk design.
Below is the new design that will be used. Fresnel
collector will still be on top
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Lunar Greenhouse (3)• The greenhouse is all one part and is inflatable - can be easily deployed and
autonomously set up before astronauts arrive. Just cover with regolith!
• Source: http://ag.arizona.edu/lunargreenhouse/CEAC Project Phase Review presentation
• Use of plants leads to an issue, however….
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Lunar Base Carbon Cycle• Q: Will the carbon dioxide from astronauts be enough to maintain farm plants?
• Developed Carbon cycle to attempt to answer this.
• Discovered that attempting to quantitatively model the cycle was too complicated and best left for
future work when more values would be known
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Supplemental & Backup Food: Soylent• To guarantee sufficient food supply for 2 years – using
Soylent as major staple food and backup.
• Approved by FDA as food, features high nutrition diet and
~550 g (w/ packaging) per day per person (2000 Cal)
• Shelf life of 2 years.
• Single shipment for 2 years for 8 astronauts is ~3200 kg.
• Just add water! (which we have in ample supply)
• Does not share digestive issues prevalent in freeze-dried
foods.
• Source: www.soylent.me
• (Soylent not a necessity)
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3D Printing• Printing process using regolith can
work in a vacuum due to capillary
forces in the soil.
• First 3D printer sent into space in
September of 2014 to test effects of
zero gravity as a proof-of-concept.
• Still too early in development to say
anything about feasibility for sure
• Allow astronauts to build tools and
spare parts
• Printing food is currently in
development with a prototype
released in October of 2014.
Made In Space’s Zero-G Printer
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In-Situ Resource Utilization (ISRU)• Consumables feature heavy reliance on ISRU to
maximize self-sufficiency
• Water ice availability on Moon open many
broad life-support options
• Several metals and metallurgic processes
available.
• 3D Printing make use of metals from ISRU very
direct
• Regolith features useful ilmenite
• Regolith agglutinate glasses and np-Fe0 open up
efficient microwave heating methods for various
uses
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ISRU – Water Ice• LCROSS mission estimated water ice content in polar
crater regolith of 5.6±2.9% water by mass (Colaprete et
al.)
• One percent water by mass is sufficient for a system as
outlined by SpaceWorks Engineering Inc.
• Mining with a system of excavating robots or a
conveyor/bucket-wheel system could conceivably
provide 2000 kg/hr of regolith
• Source: http://www.sei.aero/eng/papers/uploads/archive/IAC-07-A5.1.03_present.pdf
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ISRU – Water Ice• A simple heating, filtering, and condensing process could provide
20 kg/hr of water
• Desired ratio of water can be stored on site for immediate use or
easily electrolyzed into O2/H2 for various uses
• Equates to 166 mT/yr H2O (95% day)
• After electrolysis – 148 mT/yr O2 and 18.5 mT/yr H2
• H2 and O2 saved to be sold as fuel, but also used for portable fuel
cell use. O2 also used to supplement life support.
• Requires 112 kW to operate continuously
• Source: electricity req’t for electrolysis: http://www.fch-ju.eu/sites/default/files/study%20electrolyser_0-
Logos_0_0.pdf
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ISRU – Regolith Use
• Regolith contains many oxides and can be broken into constituents
• Can feasibly produce Ti, Fe, etc…and of course, O2
• Large quantities of ilmenite on Moon (FeTiO3) can be electrolyzed with H2 into Fe, TiO2 and H2O which can be reclaimed as H2 and O2
• Useful Fe is gained, but TiO2 is discarded
• Ti can be extracted if Cl is provided – Cl not lost through process
• Source: http://isru.msfc.nasa.gov/lib/Documents/PDF%20Files/NASA_TM_06_214600.pdf
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ISRU – Regolith Use
• How to heat regolith? Microwaves.
• 2.45 GHz microwaves excite nanophase iron (np-Fe0) in soil
• Soil heats from inside out at 1000 K/min to 2300 K
• Agglutinates glass over producing solid brick of metallic
glass, or other shapes!
• Microwave Rover could make solid roads!
• Microwaved bricks and packed soil with microwave
application would make solid, air-tight structures
• Kitchen-grade microwaves (1000 W)
• Source:
http://www.isruinfo.com/docs/microwave_sintering_of_lunar_soil.pdf
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Power BudgetEstimated Power Budget (Selected Values)
• Life Support: 14.5 kW
• ISRU
– Water: 112 kW
– Microwaves: 5 kW
• 3-D Printing: 42 kW
• Greenhouse: 4.167 kW
• Computers: 3.5 kW
• Research/Lab: 40 kW
• Kitchen: 7.5 kW
• Lighting: 2 kW
• Communications: 5 kW
For Recharging vehicles
• Lunar Rover: 2.18 kW
• Mining Rover 4.5 kW
• Lander: 4 kW
Subtotal: 246.35 kW
• Include a 5% buffer :
Total: 260 kW
• These are high estimates in an attempt
to account for currently unknown values
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Power Supply• SAFE-400 100 kW heat-pipe power
system fission reactor
– Generates more power per kilogram than solar panels.
• Current proposal fields 2 SAFE-400 reactors providing 200 kW of power
• Reactors are supplemented by 75 kW of solar arrays in nearly perpetual light to supplement reactors and maintain life support and mission-critical operations in emergencies
– Panel area: 215 m2 @ 350 W/m2
-100
100
300
500
700
900
1100
0 20000 40000 60000 80000 100000 120000
MA
SS (
KG
)POWER (WATTS)
Power vs Weight of Solar and Nuclear
Solar Nuclear
SAFE-400
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ROI Team
Technical Group Leader: Alexander Ward
Brandon Bordovsky
Chase Lookofsky
Justin Ruiz
Mathias Weeks
Taylor Dickens
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ROI: Lagrange Point Fuel Depot Concept• Send fuel to L1
• Store Cryogenic Hydrogen & Oxygen
• Refueling Capabilities
• Satellites in GEO
• Interplanetary missions
• Proof of Concept done by NASA 2011
• Robotic Refueling Mission
• Successful transfer between two satellites
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ROI: Lagrange Point Fuel Depot Business• Current Earth launch is $30000 per pound of fuel at depot
– Includes profit using Atlas V
– Heavy Atmosphere of Earth
– Must bring Large amounts of fuel
• Not used in launch
• Our System is autonomous and robotic
– High startup cost, very low cost once started
– Earth based launches of fuel could not compete
• A low cost fuel depot will affect future satellites
– Satellites will be designed to utilize this low cost fuel
• Since Satellites do not currently utilize LOX & H2
– High profit after initial investment
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ROI: Lagrange Point Fuel Depot Business• Estimations for cheaper cost
– Not going through earth atmosphere or gravity
– Robotic production with minimal involvement from earth
– Smaller refueling tanker moves between L1 and GEO
• Similar to naval infrastructure
– High Initial Cost – Low continuing costs
• There is currently no market for our fuel– We will provide a solution so superior we will create a market
– Our low cost fuel will drive satellites to new designs
• Utilize chemical rockets for station keeping
• Satellites will launch with no fuel
– Refuel at station
• Satellites launching with no fuel will cost less to companies
• The creation of new satellites will create a stable and considerable profit
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ROI: Lagrange Point Fuel Depot Process
L1
GEO
Lunar Orbit
Tertiary Depot for commercial
refuel
Flies between
GEO and L1
Primary Depot
Stationary in L1
Lunar lander
Reusable and goes between surface and
lunar orbitCommand Module
Goes between Lunar
orbit and L1
Depot in L1 will use bleed gas for station keeping
Tertiary Depot will use phasing orbits to refuel
commercial satellites
Depots lose 20% Hydrogen and 7% oxygen to bleed off
per year
All components are reused and fueled by LOX & H2
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Mining Iron• Iron is widespread on the Lunar surface
– Samples from the Apollo missions were rich
in iron as well as titanium.
– Iron can be seen by analyzing reflectance
variations where these elements absorb
irradiation.
• While iron is not rare on Earth it may be
beneficial to mine.
– A ready source of raw materials for building
would be essential for a moon base
– Iron could be something that is used for
many structural needs.
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Mining Rare Earth Elements• China is pinching the export of rare earth elements
• Returned samples do not contain concentrations directly, but can be detected
• It boils down whether it is economically viable to search for them on the
moon as opposed to searching on Earth
• Mining on the moon brings up the question of who owns the resources on
the moon
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Mining Methods• Fleet of excavating rovers could provide 2000 kg/hr of regolith
• Mining Rover
• Bucket-wheel
• Built using the LER Chariot Chassis
• Autonomous
• Battery Powered with fuel-cell capability
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Fusion Reaction for Power Generation on Earth
• Successfully performed by the University of
Wisconsin – Madison Fusion Institution
• Input: Helium isotope (Helium 3) and an isotopes of
Hydrogen Deuterium
• Byproducts: Helium atom, a proton, and a lot of
energy
• 20 % more efficient than natural gas and coal (about
seventy percent efficiency)
• No pollution
Helium 3 Mining
Alex Ward
http://io9.com/5908499/could-helium-3-really-solve-earths-energy-problems
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Helium 3 Mining Helium 3 on the Moon
• Comes from solar winds and is blocked by the Earths magnetic field
• The U.S. currently has 30 kg of Helium 3
• The Moon holds an estimated 1,100,000 metric tons
• 25 metric tonnes could power U.S. for a year. Worth about 75 billion dollars
• Can be extracted by heating lunar regolith to 600 degrees F at processing facility
• Huge potential for profit beyond Moon base program sustainment
• Current estimates of concentration within regolith: 50 parts per billion
• Extensive mining operation would be needed
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Helium 3 Transportation • Reusable/refuelable transportation system will
bring Helium 3 tanks back to Earth at low cost
• Reusable heat shielded Tanks manufactured on
Earth can be used to bring supplies to the Moon
as well as transport the Helium 3 back to Earth
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Low Frequency Radio Telescope (LFRT)Similar to ALMA radio telescopes located in Chile.
Objectives:
• Detection of extrasolar planets with similar magnetic field to Earths.
• Observe the formation of some of the earliest structure in the universe.
Advantages for lunar telescope:
• The far side of the moon is shielded from radio interference from Earth.
• Detection of larger ranges of frequency due to absence of Earth’s Ionosphere.
Possible Customers/Funders:
Harvard, the National Radio Astronomy Observatory, the University of California at Berkeley, University of Washington and NASA'sJet Propulsion Laboratory, Google, Naval Research Laboratory
Justin Ruiz
http://www.forbes.com/sites/brucedorminey/2013/08/30/nasa-sites-lunar-far-side-for-low-frequency-radio-telescope/
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Hypogravity
• When the force of gravity is less than
that on the surface of the earth
• Typically between 0 and 1 g
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Gravitational Influences• Plants
– the pull of gravity affects the direction of growth
• Animals
– Size of single biological cell inversely proportional to the strength of gravity. I.e. more gravity, smaller cell
– Gravity influences musculoskeletal systems, fluid distribution, and hydrodynamics of the circulation
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Recent Studies• Studies have shown that metabolism, the immune system and cell functions are affected by hypogravity
• Human Immune Cells unable to mature
• Reproduction may be affected
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Potential Studies• Long term effects of a hypogravity as opposed
to microgravity on humans
• More opportunities for research and
development of space agriculture
• Finding solutions for current issues regarding
long term exposure to reduced gravity
• Potential development of moon sports
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Lunar Biohazards
& Prevention
Technical Group Leader: Garrett Perez
Karel Beetge
Brookelynn Russey
Patrick McEntire
Chris White
Trevor Owen
Andrew McNeil
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Overview• Radiation
• Dust
• Hypogravity
• Pathogens and Microbes
• Training
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Radiation Hazards• Radiation poisoning
• Cancer
• Genetic Mutations
• Death
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Radiation Mitigation• Radiation protection system
• Base protection
• Astronaut Monitoring
• Plant protection
• Regolith layering
• Minimum 50cm thickness, 75 g/cm2
• Dose reduction and regolith layering
follows exponential curve
Garrett Perez
Simonsen, Lisa C. and John E. Nealy. “Radiation Protection for Human Missions to the Moon and Mars.” NASA (1991). n. pag. Web. 20 Nov. 2014.
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Radiation Mitigation• Radiation protection system
• Base protection
• Astronaut Monitoring
• Plant protection
• Exposure monitoring
• In base: radiation detectors to
corroborate charts
• EVAs: Time logs, suit radiation detectors
Garrett Perez
http://www.astrobio.net/topic/origins/extreme-life/biomex-exploring-mars-low-earth-orbit/
Simonsen, Lisa C. and John E. Nealy. “Radiation Protection for Human Missions to the Moon and Mars.” NASA (1991). n. pag. Web. 20 Nov. 2014.
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Radiation Mitigation• Radiation protection system
• Base protection
• Astronaut Monitoring
• Plant protection
• Currently under experimentation
• BIOMEX experiment on ISS
• Plants thriving in high radiation
environment around Chernobyl
Garrett Perez
http://www.bbc.com/news/science-environment-11345935
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Dust Hazards• Toxic to respiratory systems
• Abrasive to humans and equipment
• Obscures vision/camera lenses
• Chemically reactive
• Electrically conductive
Andrew McNeil
Gaier, James R. "The Effects of Lunar Dust on EVA Systems During the Apollo Missions." NASA Technical Memorandum (2005): n. pag. Web. 8 Dec. 2014.
Taylor, Lawrence A., Harrison H. Schmitt, W. D. Carrier, III, and Masami Nakagawa. "The Lunar Dust Problem: From Liability to Asset." American Institute of Aeronautics and Astronautics (n.d.): n. pag. Web. 8 Dec. 2014.
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Dust Mitigation• 4 Stage System:
• Stage 1: Dust Repellant Coverings
• Stage 2: Airlock
• Stage 3: Electrostatic Removal
• Stage 4: Mechanical Air Filtration
• Superhydrophobic coatings
• Tyvek suit covers
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Dust Mitigation• 4 Stage System:
• Stage 1: Dust Repellant Coverings
• Stage 2: Airlock
• Stage 3: Electrostatic Removal
• Stage 4: Mechanical Air Filtration
• Vacuum dust removal in airlock
• Vacuum connected to HVAC filtration
• Tool storage lockers
Andrew McNeil
Cadogan, Dave, and Janet Ferl. "Dust Mitigation Solutions for Lunar and Mars Surface Systems." SAE International (2007): n. pag. Web. 8 Dec. 2014.
DiGiuseppe, Michael, Ronald Pirich, and Val Kraut. "Lunar Regolith Control and Resource Utilization." IEEE Journal (2009): n. pag. Web. 8 Dec. 2014.
Pirich, Ronald, John Weir, and Dennis Leyble. "Self-Cleaning and Anti-Contamination Coatings for Space Exploration: An Overview." The International Society for Optics and Photonics 7069 (2008): n. pag. Web.
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Dust Mitigation• 4 Stage System:
• Stage 1: Dust Repellant Coverings
• Stage 2: Airlock
• Stage 3: Electrostatic Removal
• Stage 4: Mechanical Air Filtration
• Magnet filtration
• 70% dust removed
• Oscillating Electromagnetic Fields
• Removes 90% of dust
• 15% to 99% efficiency on solar panels
Andrew McNeil
Calle, C. I., J. L. McFall, C. R. Buhler, S. J. Snyder, E. E. Arens, A. Chen, M. L. Ritz, J. S. Clements, C. R. Fontier, and S. Trigwell. "Dust Particle Removal by Electrostatic and Dielectrophoretic Forces with Applications to NASA Exploration Missions." ESA Annual Meeting on Electrostatics O1 (2008): n. pag. Web. 8 Dec. 2014.
Eimer, B. C., and L. A. Taylor. "DUST MITIGATION: LUNAR AIR FILTRATION WITH A PERMANENT-MAGNET SYSTEM (LAF-PMS)." Lunar and Planetary Science XXXVIII (2007): n. pag. Web. 8 Dec. 2014.
Olive, Jordan. "UNDERSTANDING AND IMPROVING UPON ELECTRODYNAMIC DUST SHIELD TECHNOLOGY ON A LUNAR ROVER." Hawaii NASA Space Grant Consortium (2009): n. pag. Web. 8 Dec. 2014.
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Dust Mitigation• 4 Stage System:
• Stage 1: Dust Repellant Coverings
• Stage 2: Airlock
• Stage 3: Electrostatic Removal
• Stage 4: Mechanical Air Filtration
• HEPA filter
• 99.97% of particles 0.3μm or larger removed
• Secondary system to electrostatic removal
• Activated carbon filter for chemical and biological
contaminants
Andrew McNeil
"Addenda to ASME AG-1–2003 Code on Nuclear Air and Gas Treatment." American Society of Mechanical Engineers AG.1a (2004): n. pag. Web. 8 Dec. 2014.
Cameron Carbon Incorporated. "Activated Carbon Manufacture, Structure & Properties." (2006): n. pag. Web. 8 Dec. 2014.
TSI Incorporated. "Mechanisms of Filtration for High Efficiency Fibrous Filters." Application Note ITI-041 (2008): n. pag. Web. 8 Dec. 2014.
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HypogravityLunar Base Study Goals
• Observation of long-term effects from exposure to 1/6th g
• Medical bay/Health facility
• Integrated health monitoring system
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Hypogravity• Negative Effects:
– Bone loss
– Muscle loss
– Decreased immune system response
• Pathogen control necessary
– Cardiovascular system decay
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Hypogravity
• Why study the effects of hypogravity?
– Colonization of other planets, celestial bodies
• Moon
• Mars
– Interplanetary/Long – Duration Spaceflights
• Gravity simulation via spacecraft spin
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HypogravityIntegrated Health Monitoring
• On-body sensor suite to monitor various health aspects
• Apollo 13 movie – astronauts ripping out sensor packs
• Sensor suite must be:
• Accurate
• Comfortable
• Low power
• Wireless data transmission
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Hypogravity
Christopher White
Examples of Current ‘Wearables’
• Jawbone
• Step Tracking
• Sleep Motion
• Fitbit (pictured)
• Location Tracking
• Heart Rate
• Notification support
• Athoshttps://static1.fitbit.com/simple.b-cssdisabledjpg.h9bce7fcfed9187568cb88a34fd17d7f5.pack?items=%2Fcontent%2Fassets%2Fsurge%2Fimages%2Fgallery%2Fgallery-07.jpg
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Hypogravity
Christopher White
Examples of Current ‘Wearables’
• Jawbone
• Fitbit
• Athos
• Full – Body Sensor Suit
• Comfortable
• Wireless Transmission of Data
• Limitations
• Short Range Transmission
• Power Supply
• Ideal: Self – powered equipment
• Residual Body Heat http://blog.sfgate.com/techchron/files/2014/08/Athos_Male-Top-2_20517_REV2_RGB_HR_r2.jpg
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HypogravityWorkout Facility
• An extension of the medical bay, for close
proximity to health monitoring equipment
• Similar to ISS – Resistance
• Bicycle
• Treadmill
• Bowflex
• “Smart” equipment
• Tied into medical/base mainframe
Christopher White
http://blogs.nasa.gov/ISS_Science_Blog/wp-content/uploads/sites/207/2013/10/Top-Ten_Ten_A.jpg
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Karel Beetge
Pathogens & MicrobesPathogen Detection:
Early Warning Inc. Pathogen Sensor
• Benefits:
• Automatically detects custom array of
pathogenic bacteria and viruses that are
searched for.
• 3 hour, self-sanitizing test cycle
• Disadvantages:
• Uses 10L liquid sample in order to increase
likelihood of pathogen detection
• Does not kill pathogens
• Biochips used in detection process are
single use
http://www.earlywarninginc.com/
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Karel Beetge
Pathogens & MicrobesPathogen Detection Process
• Sample filtered, exposed to antibodies
• RNA extraction of matched microorganisms
• Reaction with DNA probes at a peak current
for each probe electrode signifies pathogen
• Custom array of pathogen detection
RNA pic: http://utcinnovationlabs.blogspot.com/2014/05/junes-molecule-of-month-rna-polymerase.html
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Ceramic Water Filter• Water treatment system
• Relies on pore size to filter debris, dirt, and
bacteria from water.
• Activated carbon core cartridge that removes
organic material and other contaminants
• Silver treatment that won’t leach away kills
viruses and bacteria
http://www.britishberkefeld.com/ceramic.html
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Pathogens & MicrobesAir Sanitizer
Airocide
• Benefits:
• Eliminates volatile organic compounds
• Kills viruses, bacteria, and airborne
microbes
• Destroys mycotoxins
• FDA Approved Class II Medical Device
• Disadvantages:
• Annual replacement of reaction chamber
• Consumes small amount of power
• Cycles small amount of air at a time per
unit size
Karel Beetge
http://www.airocide.com/filterless-technology/
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Medical Bay - Monitoring• Medical Closet
– Vitals monitoring
– Immune system monitoring
• On Person
– Seismocardiography (non-
invasive)
Brookelynn Russey
http://science.nasa.gov/media/medialibrary/2005/02/16/16feb_ultrasound_resources/figure1_med.jpg
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Medical Bay – Emergencies• Medical Kits
– Phychotropics
– Anti-inflammatory medications and
supplies
– Vitamins, prophylactic medications and
supplies
– First-aid kit
– Dressings and splints
– Antipyretics and anti-trauma medications
and supplies
– Gastroenteric and urologic medications
– Antiseptic medications
– Cardiac remedies and supplies
• Robot Assisted Surgery
Brookelynn Russey
http://i.dailymail.co.uk/i/gif/f.gif
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Training• Subjects of interest
• Base Systems
• Mining
• Evacuation
• Psychology
• Other training
Trevor Owen
• Underwater Training Mockup
• Provide astronauts with hypogravity
environment
• 1:1 scale mockup of specific equipment
• Computer systems
• Training simulations will prepare astronauts
for any circumstances
• Emergency drills
http://www.drillingcontractor.org/wp-content/uploads/2011/09/nasa015lg.JPG
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Training• Subjects of interest
• Base Systems
• Mining
• Evacuation
• Psychology
• Other training
Trevor Owen
• Geology classes
• Identify mineral and rock for missions
• Collection of rock samples in North American
Deserts
• Training in equipment purpose and use
• Training in handling of samples
• Hands-on experience in a moon-like
environment
• Trainees will wear EVA equipment
http://www.australianscience.com.au/wp-content/uploads/2013/07/mars_arizona.jpg
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Training• Subjects of interest
• Base Systems
• Mining
• Evacuation
• Psychology
• Other training
Trevor Owen
• Classroom Training
• Astronauts will be tested and quizzed on all
emergency drills
• Courses will cover topics from CPR to
emergency EVAs due to decompression
• Underwater Training Mockup
• Will provide astronauts with a physical
environment to apply textbook knowledge
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Training• Subjects of interest
• Base Systems
• Mining
• Evacuation
• Psychology
• Other training
Hayden McEntire
• Isolation Unit
• Astronauts will be required to spend 2 months
in crew isolation
• Tests astronauts’ ability to continue working as
a member of a team
• Emergency Drills
• Lunar teams will be required to complete drills
under hardship
• Inside Isolation Unit
• After physical exertion
• After long periods with no sleep
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Training• Subjects of interest
• Base Systems
• Mining
• Evacuation
• Psychology
• Other training
Hayden McEntire
• NASA training for all other procedures
• Experience in emergency procedure, daily
operation, etc. in space environment
• Training conducted for ISS living applicable to
lunar base
http://upload.wikimedia.org/wikipedia/commons/e/ee/STS-107_Classroom_Training_-_GPN-2003-00072.jpg
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Training• Subjects of interest
• Base Systems
• Mining
• Evacuation
• Psychology
• Other training
• On site training
• Run drills on location
• Decompression
• Environment monitoring
system failure
• Nitrogen leak/excess
• Solar flare
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Transportation
Technical Group Leader: Zack Zukowski
Nick Ortiz
Allison Fuss
Alejandro Azocar
Walker Hunt
Jack Theawatt
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Transportation Overview• Surface Transportation
• Off Surface Transportation
• Inter-base Transport
• Mining Rover
• Road Construction
Zach Zukowski1
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Lunar Transport Concepts
Pressurized CarUnpressurized
StandingUnpressurized
Car
http://www.nasa.gov/externalflash/moseslake/index_noaccess.html
Alejandro Azocar
No Image Available
NASA-GM Partnership
(Proprietary)
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NASA Space Exploration Vehicle (SEV)• Pressurized rover
– Shirt-sleeve environment
• Highly maneuverable
– “Crab-style” movement
– Tilting cockpit
• IVA to EVA: 15 minutes
• Carry cargo
• Docking hatch
• Modular design
http://www.nasa.gov/pdf/464826main_SEV_FactSheet_508.pdf
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SEV Specifications• Weight: 6,600 lbs.
• Payload: 2,200 lbs.
• Dim: 14.7 ft. x 13 ft. x 10 ft.
• Range: 125 miles
– Apollo: 6 miles
• 14 day life support capacity
• 72 hour solar event protection
Alejandro Azocar
http://www.nasa.gov/pdf/464826main_SEV_FactSheet_508.pdf
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Altair Lander• We have chosen to use the Altair as our
lander, which has already been planned and
designed by NASA
• We feel it will meet the needs that we have
chosen for the moon base
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Altair Specifications• Fits four crew members
• Height: 9.7 m (32 ft.)
• Landing Gear Span: 14.8 m (49 ft.)
• Diameter: 7.5m (25 ft.)
• Volume: 31.8 m3 (1,120 ft3)
• Max payload: 10,809 kg (23,830 lbs.)
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Moon Base Specifications• We will need 4 platforms to have at all times in the lunar basin. Two
will be in use for ascension and descending missions, the remaining
two will be needed for only escape missions only
• The landing sites were calculated by estimating what is used at Cape
Canaveral. The final size will be 650 m2.
• The sites will be completely glassed to avoid dust complications and
pollution
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Lunar Lander loaded with
refueling supplies
Lunar Lander makes full trip to L1 Primary Depot
Lunar Lander docks with
Command Module
Command Module brings fuel to L1 Primary Depot
Primary Depot transfer fuel to Tertiary Depot
Satellites fueled with liquid H2 and
liquid O2
Tertiary Depot brings fuel to
satellites in GEO
Satellites fueled with compressed
O2 gases
Lagrange Point Fuel Depot Trade Tree
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L1
GEO
Lunar Orbit
Tertiary Depot Primary Depot
Lunar lander
Command Module
Lagrange Point Fuel Depot Concept
As shown previously by ROI
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Lunar Lander
• Different Lunar Lander just for
non-human pay loads
• Stocked with fuel and other needed
supplies for depots
• Automated and reusable
• Will not detach from legs during
ascent
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Moon to L1 Lagrange Point
L1
Lunar OrbitPrimary Depot
Lunar Lander
Command Module
• Lunar Lander takes off from Moon’s surface,
and docks with Command Module in Lunar
Orbit
• Lunar Lander unloads supplies, descends
back to surface
• Command Module uses a Hohmann Transfer
to change trajectory towards L1
• Docks with Primary Depot at L1, and
unloads fuel and supplies
• Command Module uses another Hohmann
transfer to return to Lunar Orbit for the next
docking with the Lunar Lander
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L1 Lagrange Point to GEO
L1
GEO
Tertiary Depot
Primary Depot
• Tertiary Depot docks with Primary Depot to be
restocked with fuel
• Tertiary Depot uses instability of L1 to be put on
low energy trajectory towards GEO
• Upon reaching GEO, Tertiary Depot uses phasing
orbital maneuvers to meet with target satellite
• Tertiary Depot refuels satellite
• Tertiary Depot uses a Hohmann Transfer to return
to L1 and re-dock with Primary Depot
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Fuel and Vehicle Details• Liquid hydrogen fuel and liquid oxygen
oxidizer, that has been mined from the moon,
will be used by all spacecraft in process
• GEO satellites will be resupplied with the
liquid hydrogen and oxygen
• Fuel and oxidizer must be kept cryogenically
cooled to maintain liquid state
• Cheaper for satellites to be launched from
Earth with minimum needed fuel, then
immediately meet up with Tertiary Depot
upon reaching orbit
• All engine ignitions to be performed by
hypergolic cartridges, they may have to be
replaced during refueling process
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Inter-base Transportation• Main inter-base transport system will be
hallways between modules
• Each hallway will have safety
features in case of emergency
• At least two hallways per base
module for redundancy
• Maximum length of 8 meters
• If significantly less than 8 meters,
most safety features will not be
necessary
Inter-base Transport
HallwaysPressure difference rail
systemNone
Railing Powered walkways
Pulley systemCompressed gas
Safety Cabinet Multiple airlocks
Zach Zukowski 109
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Basic Design
Zach Zukowski 110
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Hallway Dimensions
Zach Zukowski 111
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Emergency Rail• Wire that runs from one end of the hallway to the other
• Two compressed gas powered rings to move along it quickly
• Used mostly for emergencies
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Safety Cabinet• Located halfway through the hallway
• Contains two space suits and various other equipment
• Meant to be accessed in case of emergency
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Powered Walkways• Based off the Model 1200 walkway from Mitsubishi
• Meant to assist transportation from one end to the other
• Moves 40 meters per minute
• Can be removed or turned off if it proves problematic
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Mining Rover• Continuous excavation techniques are preferable to more classic
excavators for lightweight lunar excavation. This is because the
continuous excavators do not feel the effects of soil accumulation
which degrades productivity, and they produce lower resistance
forces which enable lighter weight operation.
Jack Thweatt 115
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Scaling Excavation Properties• By scaling the capacity of the compact bucket wheel excavator,
SRs(H), built by Takraf, it is possible to estimate the capabilities
that a lunar version would have.
Bucket Wheel Diameter 3 m
Bucket Wheel Drive Power 120 kW
Belt Width .6 m
Number of buckets 12
Theoretical Capacity 480 m³/h
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Glass Roads• Np-Fe aids in the formation process at the grain level
• 2.45 GHz microwave system attached to Chassis
• Regolith road is formed in a matter of seconds
Allison Fuss
Photo courtesy of Taylor and Meek
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Fail Safe
Environment
Technical Group Leader: Hannah Fontenot
Akshay Shankar
Sachin Subramaniam
Jake Stanley
Gerald Fisher
Kevin Hainline
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ConsumablesWater
• Plumbing fails
– Limit number of joints and connections
between pipes to and from water source
• Recovery system fails
– Use H2O from fuel cells as water source
– Store backup water in crater to reclaim in
future
Food
• Resupply fails or spoils
– Three month backup of vitamin pills or
Soylent
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Consumables (2)Oxygen
• Electrolyzing system failure
– Module O2 reserve tanks
– O2 plant regeneration
• Miscalculated O2 and CO2 cycles
– O2 and CO2 management systems
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Transportation• Rover stranded during mission
– Send “rescue” rover from base
– Backup energy source on rover• Nuclear battery
• Small H2O2 rocket
– Meanwhile, limit expeditions to a certain radius,
determined by the distance base personnel can walk
on a tank of O2
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Transportation (3)• Loss of pressurized transport cartridge inside connecting hallway
– Personnel can pull themselves to airlock using overhead railway
– Moving walkways on either side of hallway
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Biohazard• Radiation exposure
• Quarantine feasible base structure
• Geiger Counters for prevention
• Easily accessible decontamination stations
• Suit rips• Self healing fabric application (requires trigger)
• Insta-patch system
• Emergency notification
• Dust entry • Multistage cleaning
• Regular scanning of air for moon dust density
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Biohazard (2)• Experimental decontamination
• Identical requirements as radiation poisoning
• Pathogen Exposure• Regular testing of air and water for harmful organisms
• Regular medical check ups for crew
• Easily accessible medical facilities and support
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Research and Operations• Resupplying Lander damage
• Back up lander prepared for all missions
• Hydrazine leakage (explosive, carcinogenic)• Instant 10 (H2O):1(N2H4) dilution w.r.t water for aqueous hydrazine
• Neutralization using 6(NaClO):1(N2H4) concentration w.r.t sodium hypochlorite
• Experimental decontamination protocol followed
• Cryogenic bleeding• Use for attitude control
• Mining bucket wheel damage• Self return to base for repair
• Site marking for restarting operation
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Base Siting and Layout
Wall break and depressurization
• Evacuation plans for all buildings
• Living space buildings
– Extra space in others to accommodate displaced crew
• Farming buildings
– More farm area than minimum required
– Consider separate farm areas
– Some repair robots stored in farming areas
• Laboratory areas
– Single airtight doors to partially isolate rooms.
Inflatable burst
• Inflatable is capable of collapsing (Meteor Strike)
– Evacuation plan as per depressurization
– Inflatable cut and contents removed
– Inflatable repaired or replaced
– Contents returned or replaced
• Inflatable cannot collapse
– Burst contained by surrounding structure
– Evacuation plan following depressurization
– Inflatable patch or replacement
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Base Siting and Layout (2)Hub unit failure
• Building connections circumventing hub
unit
• Supplemental living space
– Will not need replacement if hub is
repaired quickly
• Base computer systems
– Backup base mainframe at a different
location
SMA Structural Deployment Power Loss
• Secondary, robot assisted, deployment
method
Lack of building materials
• Always have some extra
• Plan to be capable of reducing usage
Micrometeorites and other punctures
• Self-healing materials
Airlock failure
• Between buildings
– Redundant pathways
• To exterior
– Connections to other buildings allow
egress from other locations
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In Conclusion
Crew:8 Base size: 180 m2
275 Kw of power He3 Mining
L1 Fuel Depot Earth simulation atmosphere
Chase Lookofsky
• The technology exists
• The manpower exists
• The finances are out
• DO we have the Ambition?
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References and SourcesTaylor, Lawrence A., and Thomas T. Meek. "Microwave Sintering of Lunar Soil:
Properties, Theory, and Practice." Journal of Aerospace Engineering 18.3
(2005): 188. Web.
Vollmer, Michael. "Physics of the Microwave Oven." Institute of Physics (2004): n.
pag. Simon Fraser University. Web.
http://www.thespacereview.com/article/502/1
http://www.globalsecurity.org/space/systems/lsam.htm
http://spaceflightsystems.grc.nasa.gov/EFDPO/STO/
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References and Sources (2)https://howthingsfly.si.edu/sites/default/files/image-large/A19800081000cp01_lg.jpg
http://www.nasa.gov/pdf/289914main_fs_altair_lunar_lander.pdf
http://en.wikipedia.org/wiki/Hypergolic_propellant
http://ccar.colorado.edu/asen5050/projects/projects_2012/wolma/img/earth_moon_l_pts.jpg
http://en.wikipedia.org/wiki/Hohmann_transfer_orbit
https://www.ri.cmu.edu/pub_files/2011/9/Skonieczny2011.pdf
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References and Sources (3)http://www.takraf.com/MediaLibrary/Catalog/TAKRAF/Products/References/Reference-Sheet_SRs-1050_CBWE_Brod-
Gneotino.pdf
http://astrobotic.net/2010/07/30/robotic-excavation-on-the-moon/
http://www.mitsubishielectric.com/elevator/products/basic/moving_walks/a_moving_walks/pdf/catalog_hi.pdf
http://space.io9.com/future-astronauts-might-walk-not-hop-on-the-moon-1641324551
http://www.clavius.org/gravleap.html
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