The Phoenix Project - UMD

May 23, 2006RASC-AL

University of MarylandThe Phoenix Project

The Phoenix ProjectModifying International Space Station toSupport the Vision for Space Exploration

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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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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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• 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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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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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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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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Overall Structure

Townhouse B

Townhouse A

Stability ArmsInflatable

Transfer Tube

Non-RotatingSections

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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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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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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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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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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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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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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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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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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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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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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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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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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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Townhouse Support Structure (TSS)

• Common Berthing Mechanisms (CBMs) notdesigned to support modules under gravity

• Reinforced with I-beam frames

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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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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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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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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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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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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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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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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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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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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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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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Overall Structure

Townhouse B

Townhouse A

Stability ArmsInflatable

Transfer Tube

Non-RotatingSections

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Construction – Stage I

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Construction – Stage II

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Construction – Stage III

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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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• 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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• 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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Outreach

3 Focus Areas-Campus-Community-Educational (K-12)

200*+ hours ofoutreach!

100% TeamParticipation

* Not including public PDR & CDR

Documents

The Phoenix Project - UMD