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University of MarylandThe Phoenix Project
The Phoenix ProjectModifying International Space Station toSupport the Vision for Space Exploration
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University of MarylandThe Phoenix Project
NASA Vision for Space Exploration• Manned missions to Mars following sustained
human presence on the moon• Unknowns:
– Can we sustain a crew of 6 for a 3-year Mars mission?– How will humans respond to prolonged partial gravity?– How will humans conduct experiments on the Martian surface?– What equipment is necessary to experiment in partial gravity?
• Building a space station in Low-Earth Orbit (LEO)to answer these questions would cost nearly asmuch as a manned mission to Mars.
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University of MarylandThe Phoenix Project
International Space Station (ISS)• ISS scheduled for completion in 2010
– Science modules– Structural components
(nodes and trusses)
• Money Invested
• Can we exploit this resource for simulating Marsmissions?
$ ?Russia
$ 2BCanada
$ 8BJapan
$ 10BEurope
$ 100BUSA
Image: http://en.wikipedia.org/wiki/International_Space_Station
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University of MarylandThe Phoenix Project
• Convert ISS into a new space station, maximizinguse of existing ISS components
• Station will be capable of:– Supporting a crew of 6 for 3 years without re-supply– Testing human response to partial gravity: 0g to 1g
• Station construction will begin 1 January 2017• Partial gravity testing finished by 1 January 2024• Mars mission simulation by 1 January 2027
• SSP will accomplish this for $ 13.38B
Space Station Phoenix
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University of MarylandThe Phoenix Project
Mars Mission Simulation• Fast transit mission profile
– 5 month 0g transit phase– 21 months at ⅜g on Mars surface– 4 month 0g return
• Self-sufficiency– 3 year supply of all consumables– No re-supply, except in case of emergency
• Physiological Experiments– 2 crewmembers – 6 hours/day– Endurance: treadmill use in I-suit– Dexterity: tool workstation– Adjustment: 0g to ⅜g transition
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University of MarylandThe Phoenix Project
Gravity Test• Study various effects of long term exposure to
partial gravity
• Gravities: 25%, 50%, and 75% of Earth gravity
• Topics of study– Plant growth– Cell biology– Life science– Human physiology– Rodent physiology– Mars equipment testing
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University of MarylandThe Phoenix Project
Choosing a Rotation Rate
• Lackner study demonstrated that 10 rpm can be tolerableif spatial disorientation is mitigated with head movementsduring acceleration
• Discomfort due to vestibular and ocular sense of Coriolisacceleration forces
4.5 rpm chosen to strike a balance between minimizing theCoriolis force disturbance to the crew and minimizing thesize of the rotating arms
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University of MarylandThe Phoenix Project
Overall Structure
Townhouse B
Townhouse A
Stability ArmsInflatable
Transfer Tube
Non-RotatingSections
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University of MarylandThe Phoenix Project
Townhouse A (Crew Habitat)New modules/components: Node 3B,
PMA 3Cupola
Raffaello(Galley)
Leonardo(Crew Quarters)
Node 3BRussian RM
(Crew Quarters)
Node 3A
PMA 3
Donatello(Exercise/Medical)
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University of MarylandThe Phoenix Project
Crew Quarters
Bed 1
Bed 2
MPLM: LeonardoCurtain Dividers
• 3.8 m2 of floor space per person
• Removable curtains provideprivacy
• Each bed is 2 m x 1 m
• Sleeping restraints for 0g
• Beds lofted – desks and personalstorage underneath
• At least 1.4 m3 of additionalstorage per crew member underfloor
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University of MarylandThe Phoenix Project
Galley
MPLM: Raffaello
3.86 m
3.2
m
0.97 m
0.73 m1.75 m
Fridge/Freezer
Food
Pantry/Games
FoodDrawers
FoldableTable
Water
TV/DVD
CleaningSupplies
TrashCompactor
Trash
Microwave/Heater
Food PrepArea
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University of MarylandThe Phoenix Project
Exercise/Medical
Partition
Human Research Facility I Rack
Entrance
3.86 m3.
2 m
0.97 m
0.73 m1.75 m
Medical BedRowing Machine
TreadmillErgometerExercise Mat
Supplies
MPLM: Donatello
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University of MarylandThe Phoenix Project
Food and Water
1,630 kgEmergency Supply
7,930 kgMars Simulation
Maximum Water Required: 9,560 kg
Water Recovery System
Worst Case Mass of Water Consumables
UPA – Urine Processor AssemblyWPA – Water Processor AssemblyIn order to save water for laundry,disposable clothing will be used.
Daily Food Ration : 1.55 kg, 0.0032 m3
Total Food : 11,200 kg, 23 m3
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University of MarylandThe Phoenix Project
Hygiene• Hamilton Sundstrand Waste
Collection System– Functions at all gravity levels
from 0g to 1g– Solids compacted– Waste contingency bags will be
provided in case of failure• A “Comfort” hygienic set
provided to each crew member;contains personal hygienicsupplies
• Wet towels will be used insteadof a traditional shower– Reduces water consumption– Astronauts have preferred this
method in reduced gravityconditions
Image: http://l iftoff.msfc.nasa.gov/Shared/News2001/StationPlumbing/HygieneCenter-large.jpg
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University of MarylandThe Phoenix Project
SSP Atmospheric Parameters2000 m3SSP Cabin Volume
0.07 m/s to 0.20 m/sVentilation 3.5 x 106 max counts/m3Airborne Particulates
25% to 70%Relative Humidity18.0 ºC to 24.0 ºCTemperature Range
8.3 to 14.7 psiCabin Pressure79% N2, 21% O2Major Atm. Composition
SSP Daily O2 Consumption [kg O2/per day]
0.85 (x6)Metabolic Crew O2Req.
SSP Daily CO2 Production[kg CO2/per day]
1.00 (x6)Metabolic Crew Product
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University of MarylandThe Phoenix Project
Atmospheric Life Support
Sabatier ReactorCO2 Reduction2-Bed Molecular SieveCO2 Removal from Cabin
Solid Polymer Water Electrolysis (SPWE)O2 Generation/SupplyDisassociation of liquid hydrazine (N2H4)N2 Generation/Supply
N2H4 Disassociation
SPWE
2-BMS
Sabatier
Pressure Control
Assembly
SSP
CABIN
N2
O2
CO2
H2
H2O Crew PackageTank
CH4 (Vented)
H2O
H2O
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University of MarylandThe Phoenix Project
Atmospheric Life Support RacksOxygen Generation System
(OGS) – ON ISSAir Revitalization System
(ARS) – ON ISS
10.08 kg/day H2ONeeded to generate O2
using SPWE
4.88 kg/day H2OReclaimed by Sabatier
711 kgMass
3.153 kWPower
480 kgMass
1.90 kWPower
-OGS and ARS located together on Node 3 of both Townhouse A and B-
OGS: SPWE and Sabatier ARS: 2-BMS, Trace ContaminantControl System, Mass Spectrometer
Image: “OGA Graphic”, Hamilton Sundstrand Space Sy stems International, 2005 Image: “ISS AR Rack”, NASA/TM-1998-206956/VOL1
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University of MarylandThe Phoenix Project
Emergency SystemsCaution and Warning
System (CWS)• Provides visual and audible cues tothe following emergencies:
• Fire
• Hazardous Atmosphere
• Depressurization
• General Caution
• Currently on all ISS modules aspush button panels
Fire Detection/Suppression(FDS)
• Photoelectric smoke detectors arelocated on node/cabin vents
• Upon fire detection, ventilation isautomatically ceased to fire location
• Fire can be suppressed usingonboard CO2 portable fire extinguishers(PFE)
•All FDS systems existing on the ISSImage: Whitaker, Ov erv iew of ISS U.S. Fire Detection and Suppression Sy stem ,NASA/JSC
Image: NASA/TM-1998-206956/VOL1
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University of MarylandThe Phoenix Project
Two-Fault Atmosphere Supply Backup O2 Generation
Full MissionSecond OGS
15 min/PBAPortable BreathingApparatus (PBA)
28 daysLiClO4 “Candles”
DurationAuxiliary System
Backup CO2 Removal
Full MissionSecond ARS
28 daysLiOH Canisters
DurationAuxiliary System
LiClO4 Candle
PBA
Image (Top Right): “Molecular Ltd.”http://www.molecularproducts.co.uk/v2/products/candle_33/specs.htmImage (Lower Right): “PBA”, Whitaker, Overview of the ISS US Fire Detection and Control System
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University of MarylandThe Phoenix Project
Townhouse B (Science)New modules/components: Node 3C
JEM PM
JEMELM-PS
Node 3CU.S. Lab(Destiny)
Node 2Columbus
(Mars SimulationModule)
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University of MarylandThe Phoenix Project
Racks in Science Townhouse
• Human Research Facilities 1 and 2• Microgravity Science Glovebox• Plant Biotechnology Facility• Mars Research Equipment Test Facility• Rodent Research Facility• Japanese Multi-User Experiment Facility
Image: http://hrf.jsc.nasa.gov/Image: http://wcsar.engr.wisc.edu/cpbf.html
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University of MarylandThe Phoenix Project
Townhouse Support Structure (TSS)
• Common Berthing Mechanisms (CBMs) notdesigned to support modules under gravity
• Reinforced with I-beam frames
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University of MarylandThe Phoenix Project
Inflatable Transfer Tubes• Shirtsleeve environment for transferring crew between
townhouses• Cover 90 m span in two sections, each connecting to a
townhouse and the central node• Maximum pressure differential of 14.7 psi• Inflatables up to much lighter than solid aluminum pressure
vessel• Crew has choice of motorized lift and rope later for
movement through tubeTotal interior volume: 330 m3
Total interior surface area: 610 m2
Total soft-goods mass: 1240 kg
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University of MarylandThe Phoenix Project
Central Axis
Central Axis does not spin withrest of station
Node 1
Pressurized MatingAdapter (PMA) 5
Counter Rotating Assembly(CRA)
PIRSS6 Truss
Propulsion Package
CRA
P6 Truss
Propulsion Package
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University of MarylandThe Phoenix Project
Stability Arm
• Required for station stability (Moment of Inertia)• Acts much like the stabilizer bar on a two-bladehelicopter rotor
MLMPMA 4
U.S. AirlockPMA 2
Crew Tank Package
PMA 1
Zvezda
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University of MarylandThe Phoenix Project
Spin Stability• About the principal axes,
the moment of inertia tensor• The angular difference
between the principal andgeometric z-axis 0.3°
• On the z-axis, center ofgravity 1.03 m below centerof Node 1
• Center of gravity on Node 1in the x-y plane (requiredfor docking)– within 0.08 m on the y-axis– within 0.01 m on the x-axis
X
Z
Y
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University of MarylandThe Phoenix Project
Docking Stability• Higher stability needed during docking• Requires large torques for short durations prior to
dock, when station is spinning• ISS chemical thrusters and tanks and mount them
along x-axis• Will require 375 kg of propellant (N2O4 / UDMH)• Following thruster firing:
– Max ground accelerations = 12% perceptible levels– Max inertial truss deflection = 1.94 º
• Normal operation (nutation from thruster inaccuracydamped out)– Max ground accelerations = 6.6% perceptible levels– Max inertial truss deflection = 0.60º
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University of MarylandThe Phoenix Project
Propulsion and Station Spin• P&W T-220HT
– Hall-Effect Thruster– Operates with a specific
impulse of 2,500 s– Will produce 12N– Liquid xenon propellant– 8 thrusters will be used
for spinning
28.8¾g0g5.3½g¾g6.9¼g½g
16.60g¼g20.30g⅜g
Time(hours)
CurrentGravity
DesiredGravity
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University of MarylandThe Phoenix Project
Station Orientation• SSP stays at ISS orbit• Orientation is orthogonal to Earth-Station orbital radial
direction while its rotation axis projection onto Earth-Sunorbital plane points toward center of the Sun– Reduced solar array movement– Compensate for Earth gravity gradient by positioning smallest
moment of inertia axis toward Earth’s center– Reduced thermal loads and gradient– Fewer communication antennas
Rotation Axis
Earth StationPlane
Earth OrbitStation Orbit
Sun EarthPlane
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University of MarylandThe Phoenix Project
Attitude and Orbit Maintenance• Main perturbations
– Magnetic field force, Solar radiation pressure and Docking torques
• Drag causes a Δv of 108 m/s per year• Total Xenon Mass : 24,600 kg
0.260.14Docking (kg/dock)1833,010Perturbation (kg/year)
SpinningNot SpinningXenon mass
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University of MarylandThe Phoenix Project
Power Systems• Solar panels: SLASR
(Stretched Lens ArraySquare-Rigger)– Power (EOL): 294 kW– Mass: 1,275 kg– Area: 1,400 m2
• Batteries: Ni-H2
– 90% efficiency– 40% depth of discharge– Mass : 3,330 kg
Image: http://www.entechsolar.com/IACSLASR.pdf
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University of MarylandThe Phoenix Project
Communications• Four directional antennae relay
two HDTV channels and16Mbps of data through theTDRSS network to the ground.
• A backup system provides lowbandwidth communication toTDRSS and directly to theground with antennae that areomni-directional, ensuring thatcontact with SSP will never belost.
• Communications withapproaching vehiclesaccomplished through existingsystems on Destiny
Antennas
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University of MarylandThe Phoenix Project
Thermal Systems
• Need to dissipate 164 kW of heat• 165 kW of heat dissipation
– 8 PVR radiators• 1,060 kg each• 11.5 kW rejection each
– 6 HRS radiators• 1,220 kg each• 11.8 kW rejection each
• Total radiator mass: 15,800 kg
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University of MarylandThe Phoenix Project
Overall Structure
Townhouse B
Townhouse A
Stability ArmsInflatable
Transfer Tube
Non-RotatingSections
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University of MarylandThe Phoenix Project
Mission Timeline
10987632
2026202520242023202220212020201920182017Year
Month
Phase
Stage
GravityCrew #
Mission C
omplete: Jan 2027
AugApr
JulyFeb
Mar
May
Jul
Sep
Jul
Jan
Mars MissionSimulation
Partial GravityExperimentationConstruction
ReturnSurface
TransitIIIIIIIIIIII
038%075%50%25%0
Reserve Tim
e
131211541
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University of MarylandThe Phoenix Project
• Manned– Crew Launch Vehicle (CLV)– Carries Crew Exploration Vehicle (CEV)
• Cargo– Boeing Delta IV Family
Launch Details
Image (Left): Exploration System Architecture Study. National Aeronautics and Space Administration. NASA-TM-2005-214062, November 2005Image (Right): Delta IV Payload Planners Guide. Boeing Corporation. MDC 00H0043, October 2000
Cost
$1509,44610,250 1Delta IV Medium+ 5,2
$3,750314,559347,50016Total
$ 3,302282,822 312,00013Delta IV Heavy
$16011,122 13,500 1Delta IV Medium+ 5,4
$13811,16911,750 1Delta IV Medium+ 4,2
( $M )UtilizedCapacityPayload ( kg )
LaunchesVehicle
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University of MarylandThe Phoenix Project
• Budget $20B
• Under budget by 33% ($ 6.62B)• Using 79% (360,000 kg) of ISS mass• Recovering a significant portion of ISS investment• Building SSP without ISS requires additional $ 99B
Conclusion - Costs and Savings
$ 3.75BCargo Launches
$ 13.38BTotal$ 4.50BManned Launches
$ 1.77BGround Control$ 1.85BManufacturing$ 1.47BResearch & DevelopmentCost ($2006)Category
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