Constellation Program Overview

October 2008

hris Culbertanager, Lunar Surface Systems Project Office

ASA/Johnson Space Center

Ares V -Heavy

LiftLaunch Vehicle

Ares V -Heavy

LiftLaunch Vehicle

Ares I -Crew

Launch Vehicle

Ares I -Crew

Launch Vehicle

Earth Departure

Stage

Earth Departure

StageOrion -Crew

Exploration Vehicle

Orion -Crew

Exploration Vehicle

Altair Lunar Lander

Altair Lunar Lander

Constellation Program

Established Lunar TransportationArchitecture Point of Departure:

Provides crew & cargo delivery to & from the moonProvides capacity and capabilities consistent with candidate surface architecturesProvides sufficient performance marginsRemains within programmatic constraintsResults in acceptable levels of risk

Established Lunar TransportationArchitecture Point of Departure:

Provides crew & cargo delivery to & from the moonProvides capacity and capabilities consistent with candidate surface architecturesProvides sufficient performance marginsRemains within programmatic constraintsResults in acceptable levels of risk

Establish Lunar Surface Architectures Strategies which:

Satisfy NASA NGO’s to acceptable degree within acceptable scheduleAre consistent with capacity and capabilities of the transportation systemsInclude set of options for various prioritizations of cost, schedule & risk

Establish Lunar Surface Architectures Strategies which:

Satisfy NASA NGO’s to acceptable degree within acceptable scheduleAre consistent with capacity and capabilities of the transportation systemsInclude set of options for various prioritizations of cost, schedule & risk

Lunar Capabilities Concept Review

Transportation System

Ares I ElementsStack Integration• 2M lb gross liftoff weight• 325 ft in length• NASA-led

Upper Stage• 305k lb LOX/LH2 stage• 18 ft diameter• Aluminum-Lithium (Al-Li) structures• Instrument Unit and Interstage• Reaction Control System (RCS) / roll

control for first stage flight• Primary Ares I control avionics system• NASA Design / Boeing Production

First Stage• Derived from current

Shuttle RSRM/B• Five segments/Polybutadiene

Acrylonitride (PBAN) propellant• Recoverable• New forward adapter• Avionics upgrades• ATK Launch Systems

Upper Stage Engine

• Saturn J-2 derived engine (J-2X)• Expendable• Pratt and Whitney Rocketdyne

Orion CEV

Interstage

Instrument Unit• Primary Ares I control

avionics system• NASA Design / Boeing

Production

DAC 2 TR 5

Orion Spacecraft OverviewMission SummaryMax Crew 4 (lunar), 6 (ISS)Crewed Mission Duration 21.1 daysISS GLOW Limit 27,676 kgLunar GLOW Limit 30,257 kgTLI Control Mass 20,185 kgLoaded SM Delta V (lunar) 1,492 m/sTank Sizing Delta V (lunar) 1,560 m/s

Mission SummaryMax Crew 4 (lunar), 6 (ISS)Crewed Mission Duration 21.1 daysISS GLOW Limit 27,676 kgLunar GLOW Limit 30,257 kgTLI Control Mass 20,185 kgLoaded SM Delta V (lunar) 1,492 m/sTank Sizing Delta V (lunar) 1,560 m/s

Configuration (606D)Pressurized Volume (Total) 19.4 m3 (686 ft3)SM Propellant MMH/N2O4CM Propellant HydrazinePayload (Pressurized Lunar Return) 100kgRadiator Area 20.25 m2 (218 ft2)CM Batteries 6 x 55 A-hrLoaded CM Prop (Lunar) 146 kgSM Batteries 2 x 55 A-hrSolar Array Diameter 5.84 mLoaded SM Prop (Lunar) 8,185 kgOME Isp (Mean) 326 s

Configuration (606D)Pressurized Volume (Total) 19.4 m3 (686 ft3)SM Propellant MMH/N2O4CM Propellant HydrazinePayload (Pressurized Lunar Return) 100kgRadiator Area 20.25 m2 (218 ft2)CM Batteries 6 x 55 A-hrLoaded CM Prop (Lunar) 146 kgSM Batteries 2 x 55 A-hrSolar Array Diameter 5.84 mLoaded SM Prop (Lunar) 8,185 kgOME Isp (Mean) 326 s

CEV +X

CEV +Z

STA 1000.00CLV I/F

Orion Stack(Launch Configuration)

SA627 kg

SA(Jettisoned)

1,012 kg

CMISS: 9,525 kg

Lunar: 8,732 kg

SMISS: 8,808 kg

Lunar: 12,510 kg

LAS7,260 kg

Element Mass Targets

Current Mass EstimatesISS GLOW: 25,779 kg (Predicted)ISS Injected: 17,629 kg (Predicted)

Lunar GLOW: 29,954 kg (Predicted)Lunar Injected: 21,804 kg (Predicted)Lunar TLI: 19,927 kg (Predicted)

Altair Lunar Lander

Interstage

Solid Rocket Boosters (2)• Two recoverable 5.5-segment

PBAN-fueled, steel-casing boosters (derived from current Ares I first stage

J–2X

Payload Shroud

RS–68BEngines

(6)

Loiter Skirt

Earth Departure Stage (EDS)• One Saturn-derived J–2X LOX/LH2

engine (expendable)• 10 m (33 ft) diameter stage• Aluminum-Lithium (Al-Li) tanks• Composite structures, Instrument Unit

and Interstage• Primary Ares V avionics system Core Stage

• Six Delta IV-derived RS–68B LOX/LH2engines (expendable)

• 10 m (33 ft) diameter stage• Composite structures• Aluminum-Lithium (Al-Li) tanks

Gross Lift Off Mass: 3,704.5 t (8,167.1k lbm)Integrated Stack Length: 116 m (381 ft)

Payload Adapter

Two representative configurations shownMultiple configurations for adding a 6th Engine being traded

Ares V Concept

Altair Lunar Lander

• 4 crew to and from the surface• Seven days on the surface• Lunar outpost crew rotations

• Global Access Capability• Anytime return to Earth• Capability to land 14 to 17 metric tons of dedicated cargo

• Airlock for surface activities

• Descent stage:• Liquid oxygen / liquid hydrogen propulsion

• Ascent stage:• Hypergolic Propellants or Liquid oxygen/methane

Altair Crewed Vehicle Concept

DM LH2 Fuel Tank (x4)

DM Main Engine

Landing Leg (x4)

Pressurant Tank (x2)

Thermal Insulation

LOX Tank Support Cone (x4)

Life Support Oxygen Tank

RCS Tanks

Avionics boxes (x2)AM Connecting

Structure (Remains on DM)

Radiator (x2)

DM RCS Thruster Pod (x4)

Airlock Egress Hatch

AM-Airlock Connecting Structure

Airlock

Crew Display Monitor

Hammocks

Storage Lockers

Lunar Sample Box

Trash Bag Storage

Hand Controls

Windows

EVA Hatch

Airlock Module / Descent Module Adapter

Storage Lockers

EVA Suit Storage

Umbilical

EVA System (Suit) is Integral

Science

Removed Body Seal Closure

Removed Hip Bearings

Thigh Disconnect Retained for modularity

Two ‘shortie‘ cores

Shoulder bearing retained for mobility

IVA Gloves

Change to soft rear entry design

LEA/Microgravity EVA Suit(Configuration 1)

* Modular, reconfigurable, component-based architecture that meets various mission objectives

Lunar Surface EVA Suit(Configuration 2)

Common helmet

Common lower arms

Common legs/boots

PLSS (8 Hr EVA)

Enhanced shoulder mobility

Rear entry hatch

TMG/MLI for relevant environment – incl. boot covers

Waist Bearing

Multi-hip Bearing

EVA Gloves

Configuration 2 Suit is utilized for all phases of the lunar mission, i.e., transportation and lunar surface operations

EVA System Architecture

Sizing: Altair ΔV for LOI1,000 m/s (3,281 ft/s)

<5.8d~4d

MOONMOON

EARTHEARTH

LLO 100 km (54nm)

ERO up to 241km (130nm), minimum 222 km, LEO attitude = Gravity Gradient

1 - 5 d

EDS Performs TLI 3,175 m/s (10,417 ft/s)

1-5d 7 d

Ascent1,881 m/s (6,171 ft/s)

3-burn LOI1-5 days Altair LLO loiter

100 kg (220 lbm) pressurized return payloadTBD hrs post lunar ascent

Ares-I Delivered Mass 23.6 t (52,070 lbm)4 days LEO loiter

EDS TLI Injection Capability 66.1 t (145,726 lbm) + 5 t reserve

-20x185 km (-11x100 nm), 29º

Altair TLI Injected Control Mass 45 t (99,200 lbm)

≥ 90 min.

Altair Performs LOI1,000 m/s (3,281 ft/s)

(Propellant load for 950 m/s)

TEI 1,492 m/s (4,895 ft/s)(Tanks sized for 1, 560 m/s (5,118 m/s)

Orion• Orion TLI Control Mass 20,185 kg (44,500 lbm)

1d

7 d

Descent ΔV 2,030 m/s (6,660 ft/s)LH2/LO2 descent engine restartable/throttleable

Example of short stay Design Reference Mission

Mission Key Driving Requirements

Ares-V Extensibility to Mars Missions

• Mars Architecture study conducted during 2007 in parallel with LAT-1 and LAT-2

• Key Emphasis:– Update Mars reference architecture– Assess strategic linkages between lunar and Mars

strategies and systems• Launch Vehicle Assessments Included:

– Staging altitude– Payload size (length and diameter)– Launch rate and frequency– Delivery of both Mars payloads and using the

Ares-V shroud as the Mars entry aeroshell• Bottom Line:

– Ares-V 51.xx series launch vehicles provide adequate performance (130+ t)

– Total number of Ares-V launches per Mars mission: 7+ with a launch frequency of 30 days or less

– Shroud volume is a key driver (10 m x 30 m)• Further Assessments:

– Further refinement of Dual use shroud concept– Further refinement of mission payload strategies

and in-space transportation concepts

51.00.47 Performance Summary

Lander/Ballast Allocation

136.9

51.00.47 Gross LEO Payload

161.8

Aero-Shroud 50.0

Lander/Ballast Allocation

89.6

ASE7.9

ASE5.2

Performance Margin

13.7

Performance Margin

9.0

0

25

50

75

100

125

150

175

200

Reference 51.00.47 to 222km Dual-Use Aero Shroud to 407km Jettisoned Aero Shroud to 407km

Mas

s (t)

45/30/2008 9:39:21 AM

51.00.47: Performance Summary

Total = 153.8 t

- Baseline vehicle flies to lower orbit than Dual Use Shroud mission [222km (120nmi) circ vs. 407km (220nmi) circ]- Baseline 51.00.47 LEO payload (EDS propellant and Lunar Lander) is reported as ‘Gross Payload’.- Vehicles are structurally sized to accommodate larger shrouds.

Total = 158.5 t

51.00.48 Performance Summary

Lander/Ballast Allocation

130.8

51.00.48 Gross LEO Payload

154.3

Aero-Shroud 50.0

Lander/Ballast Allocation

83.6

ASE7.6

ASE4.8

Performance Margin

13.1

Performance Margin

8.4

0

25

50

75

100

125

150

175

200

Reference 51.00.48 to 222km Dual-Use Aero Shroud to 407km Jettisoned Aero Shroud to 407kmM

ass

(t)

55/30/2008 9:39:21 AM

51.00.48: Performance Summary

Total = 146.8 t

- Baseline vehicle flies to lower orbit than Dual Use Shroud mission [222km (120nmi) circ vs. 407km (220nmi) circ]- Baseline 51.00.48 LEO payload (EDS propellant and Lunar Lander) is reported as ‘Gross Payload’.- Vehicles are structurally sized to accommodate larger shrouds.

Total = 151.5 t

Surface Systems

Outpost Capabilities

• Habitation systems that will support a crew of 4 for 180 days onthe lunar surface

• Demonstrated ability to produce ISRU based oxygen at a rate of 1 t per year

• Unpressurized rovers that can be operated autonomously or by the crew

• Pressurized roving systems that can travel for hundreds of kilometers from the Outpost

• Power – at least 35 kW of net power production and storage for crewed eclipse periods

• Surface based laboratory systems and instruments to meet science objectives

• Sufficient functional redundancy to ensure safety and mission success

Driving Surface Architecture CharacteristicsDriving Surface Architecture Characteristics

Pervasive Mobility– Science enabler / range extender– Ability to adapt outpost elements to more locations on the lunar surface– Always something new to explore

Mission Flexibility– Minimally functional outpost capability established as early as possible– Outpost can be built at any rate with steadily increasing capabilities: “go as you pay”– Outpost can recover rapidly from loss of elements (modular and reconfigurable)– Outpost buildup can be adjusted to accommodate changing science & mission

priorities

Global Connectivity– The ability to perform global lunar exploration via sorties and long distance roving– HD cameras & High bandwidth communications– International, commercial & university participation– Virtually connecting the above to engage scientists & the general population on both

Globes

Long Duration– More time for Science– Highly reliable systems– Minimize logistics needs

• In-Situ Resource Utilization, recycling• Commonality, repair at board level

– Outpost can be implemented to emulate Mars surface scenarios– Core technologies and operations applicable to Mars exploration

17Presentation date here

ATHLETELong-distance

Mobility System (2)

ATHLETELong-distance

Mobility System (2)

Small PressurizedRover (SPR)

Small PressurizedRover (SPR)

HabitationElement

HabitationElement

Common AirlockWith Lander

Common AirlockWith Lander

ISRU OxygenProduction Plant

ISRU OxygenProduction Plant

Power Support Unit (PSU)( Supports / scavenges from

crewed landers )

Power Support Unit (PSU)( Supports / scavenges from

crewed landers )PSU

(Facilitates SPR docking & charging)

PSU(Facilitates SPR

docking & charging)

HabitationElement

HabitationElement

LogisticsPantry

LogisticsPantry

Unpressurized RoverUnpressurized Rover

10 kW Array (net)10 kW Array (net)

2 kW Array (net)2 kW Array (net)

Conceptual Full Lunar Outpost Conceptual Full Lunar Outpost

Surface Architectures Assessed

The various Surface systems can be combined in a very wide variety of options. Three surface architectures were developed in support of LCCR:

Rapid Outpost Buildup (Trade Space‐1)• Deliver as much outpost capability as soon as transportation system permits• Full‐up outpost based on the recommendations from LAT‐2.• Substantial robustness through element duplication

Initial Mobility Emphasis (Trade Space‐2)• Temper outpost build‐up based on affordability with initial emphasis on mobility 

capabilities• Full‐up outpost has less volume and limited eclipse operating capability than TS1 • Robustness achieved through functional reallocation 

Initial Habitation Emphasis (Trade Space‐3)• Temper outpost build‐up based on affordability with initial emphasis on core 

habitation & exploration capabilities• Full‐up outpost has less volume and limited eclipse operating capability than TS1 • Robustness achieved through functional reallocation 

Lunar Transportation Figures of MeritPerformance

Ability to support the lunar outpostMass to surface: crew & cargoRobustness of margins by systemSurface coverage: global access

3CxAT_Lunar TIP 06 May 2008

Ares-V Options*, Altair Mass* vs. Surface Access -->50% Temporal, 2nd TLI Opp, 1day Pre-TEI Loiter, +4 Days Post LOI Loiter

42500

43500

44500

45500

46500

47500

48500

49500

0 10 20 30 40 50 60 70 80 90 100

% Lunar Surface Access

Alta

ir M

ass

(kg)

51.0.47=74.7 mT - 20.2 mT (Orion) - 5 mT (L3 PMR) = 49.5 mT

51.0.40=69.7mT - 20.2 mT (Orion) - 5 mT (L3 PMR) = 44.5 mT

51.0.48=71.1 mT - 20.2 mT (Orion) - 5 mT (L3 PMR) = 45.9 mT

Crew Optimized, 44185 kg, 891 m/s

Cargo Optimized, 46264 kg, 891 m/s

47139 kg, 1000 m/s

100% Temporal, 5th TLI Opp 90% Temporal, 2nd TLI Opp 50% Temporal, 2nd TLI Opp

Crew Optimized, 45765 kg, 950 m/s

51.0.46=68.6mT - 20.2 mT (Orion) - 5 mT (L3 PMR) = 43.4 mT add loiter add loiter

subtract 1 mT M

R

subtract 1 mT M

R

of f load prop & subtract 1mT MR

Crew Optimized minus 1mT MR, sized for 1000 m/s, off load prop to 950 m/s, + 4 days LOI loiter, 44757 kg, resultant Cargo = 14.7 mT

Crew Optimized minus 1mT MR, sized for 950 m/s, + 4 days LOI loiter, 43485 kg, resultant Cargo = 13.0 mT

43002 kg, Cargo Capability 12.9 mT

Effects of Reducing Altair MR

* L3 Reserves applied to Ares-V and Altair,Altair Masses include 860 kg spacecraft adapter

13

Maximum LOI Loiter Case(6 Days Extended Post-LOI Loiter; No Extended TEI Loiter)

950 m/s LOI ΔV Capability 1000 m/s LOI DV Capability

AltairOnly

IntegratedAltairand

Orion

AffordabilityDDT&ERecurringBudget wedge left for surface systemsCost confidence

Page 56May 21st, 2008 SENSITIVE BUT UNCLASSIFIED (SBU)

LCCR-M (Trade Set 2) Cx Level Sandchart

$0

$2,000

$4,000

$6,000

$8,000

$10,000

$12,000

$14,000

FY08 FY10 FY12 FY14 FY16 FY18 FY20 FY22 FY24 FY26 FY28 FY30Fiscal Year

RY

$M

Lunar Surface SystemsProgram ReservesAltairEVAGround OperationsProgram IntegrationMission OpsAres VAres IOrionTotal NOA

Page 20May 21st, 2008 SENSITIVE BUT UNCLASSIFIED (SBU)

$0

$500

$1,000

$1,500

$2,000

$2,500

FY06 FY07 FY08 FY09 FY10 FY11 FY12 FY13 FY14 FY15 FY16 FY17 FY18 FY19 FY20

RY

$M

Ares V PPBE10 MarkPPBE10 Submit (51.0.39)51.0.4751.0.4851.0.4051.0.46

Ares V PMR Implications

$0

$100

$200

$300

$400

$500

$600

$700

$800

FY06 FY07 FY08 FY09 FY10 FY11 FY12 FY13 FY14 FY15 FY16 FY17 FY18 FY19 FY20

RY

$Ms

45.0.2 / 51.0.3951.0.4751.0.4851.0.4051.0.46

♦The various Ares V Options each have an impact to the Ares V Project Mark and the Ground Operations Project Mark

Ares V Project Spreads

ROM Ground Ops Development (Portion of Mark)

Phasing Challenge Relative to Mark

Note – Based on 4/24 Ground Operations input. Update received 5/14 but not included in PMR analysis. Also assumes 51.0.39 same impact as 45.0.2; to be refined

RiskLOC / LOMTechnical performance riskSchedule riskCommonality

Page 8May 21st, 2008 SENSITIVE BUT UNCLASSIFIED (SBU)

Multiple casesTOTAL Program thru HLR (Phase Correlation)

Allocated from 'Risk Over TIme Allocation'Calculated with 3500 iterations

0%10%20%30%40%50%60%70%80%90%

100%

70,000 75,000 80,000 85,000 90,000 95,000 100,000 105,000 110,000

TY $M

Conf

iden

ce L

evel

(CDF

)

Baseline with 51.0.48 option Allocated Budget thru HLR 65% Confidence Level

Current Cx Confidence Level Through HLR(Alternate Ares V Option – 51.0.48)

Note – 51.0.48 HLR confidence analysis assumes 51.0.39 uncertainty s-curve.

Markers: ConfidenceAllocated Budget (Through HLR) 83,796.65$ 25%65% Confidence Level 90,311.50$ 65%Delta between 6,514.84$

11

Trade Studies Attacked Risk Drivers of Minimal Functional Vehicle (aborts were “off the table”)

A 

Task Option Risk Build‐Up by Subsystem

0.00E+00

5.00E‐02

1.00E‐01

1.50E‐01

2.00E‐01

2.50E‐01

3.00E‐01

Baseline 100 200 300 400 500 600 700 800 900 1000 1100 1200 1300 1400 1500 1274 :

LDAC‐2

1273  :

Design

Mass Increase [kg]

LOC

MMOD

Li fe Support

Thermal

Propulsion

Power

Avionics

Preliminary Results subject to revision during close‐outResults do not include placeholdersPreliminary Results subject to revision during close‐outResults do not include placeholders1 in 71 in 7

LDAC 2LDAC 2

Increasing Mass for LOC/LOM mitigationIncreasing Mass for LOC/LOM mitigation

Operations / ExtensibilityFacilities impactsOperational flowsMars feed-forward

18For NASA Internal Use Only

CO

NST

ELLA

TIO

N G

RO

UN

D O

PER

ATI

ON

SGround Systems Discriminators

ROM Development Costs thru 2020

0

500,000

1,000,000

1,500,000

2,000,000

2,500,000

3,000,000

3,500,000

Baseline 45.0.2 51.00.40 51.00.46 51.00.47 51.00.48

VIE

SRPE

SPE

LPE

MLE

Operations

10May 20, 2008 - -

Ares -V 51.xx Series Performance

§ Follow-on analysis of CxAT_Lunarlaunch concepts applicability to Mars

§ 51 series of Ares- V launch vehicles provides better performance to LEO

§ Use of off- loaded lunar- derivative EDS reduces available shroud volume

§ Payload shroud volume limits inhibit maximum performance to Mars

388.9'

98.4'

179.1'

215.6'

74.9'

33.0'408.9'

98.4'

233.7'

76.8'

33.0'

192.5'

408.4'

98.4'

233.8'

76.2'

33.0'

192.6'

50.050.050.0Shroud to LEO (t)83.689.679.0Payload (lander) to LEO (t)

Dual-Use Shroud130.8136.9126.4Payload to LEO (t)

Jettison Shroud51.00.4851.00.4751.00.40

LEO defined as 407 km circular

Assumed Shroud:Outer Diameter: 10 mBarrel Length: 18 mOverall Length: 30 m

Surface Scenario: Figures of Merit

A comprehensive set of high-level FOMs must cover four or five major areas:

– Affordability - Comparison(s) between the projected costs of the campaign and the projected budget

– Benefit - Measure(s) of the total worth or value produced by the campaign across all themes of interest; including direct benefit items (e.g. science, operation experience, and public engagement) and indirect benefit items (e.g. extensibility to other destinations, enablement of future lunar activities)

– Safety & Mission Assurance - Measure(s) expected losses due to the uncertainty or reliability of the system

– Programmatic Risk - Evaluation of the likelihood and consequence of changes in the performance of the campaign due to multiple types of programmatic uncertainty (component performance, technology development, schedule, budget, reliability, etc.)

– Sustainability - Measure(s) of the campaigns ability to maintain a level of value (or perceived value) over time that justifies continued investment in the program

0

200

400

600

800

1000

1200

1400

1600

-50% -25% -10% 0 +10% +25% +50%0

5000

10000

15000

20000

25000

30000

35000

40000

Percent Change in L&M Mass (%),L&M + Container Mass (kg)

Cum

ulat

ive

Cre

w S

urfa

ce T

ime

(day

s)

Start

105010801080108010801080

254325355380390410

1080

375

Unallocated Lander C

apacity (kg)

Campaign Sensitivity

ObjectiveDetermine sensitivity of campaign to

variations in sparing and maintenance mass requirements from current

baseline.

AssumptionsL&M required for all elements was varied by +/-10%, +/-25%,

+/-50%.

Campaign BehaviorReduction in L&M required will allow slight increases in

crew days because of the reduction of pressurized L&M, along with significant increases in available mass.

Small decreases in L&M requirements lead to slight losses of crew days and significant reduction in available

mass.

Large increases in L&M requirements result in significant loss of crew days and available mass.

Logistics & Maintenance mass is a primary driver on campaign performance.

Campaign level analysis when combined with a “bottoms-up” element level assessment is

required to yield a more refined L&M strategy.

13807 kg 20542 kg 24350 kg 27392 kg 30053 kg 37607 kg 44088 kg

GES Extensibility Objectives

18021201918171615

Demonstrate assembly of habitat elements

Demo surface communications capability

Demo mobility for unloading/moving elements

108

Demo long-dist, pressurized mobility capability

Demo long-distance surface navigation

Test equipment repair techniques

Demo ISRU excavation processesDemonstrate Solar Power SystemDemonstrate Nuclear Power SystemCryo Fluid Storage and Distribution

Demo a high performance EVA suitDemo sustained EVA schedulesDemo long-distance EVA NavigationDemonstrate suit durability/repair activitiesDemo high use airlock or suitlockDemo robots that supplement astronaut activitiesUnderstand MTBF of equipment

Demo commonality and scavenging of sparesDemo remote training systemsDemo teleoperations capabilitiesLearn how to best perform basic working tasksDemo production of ISRU ConsumablesDemo production of ISRU Propellant

Demonstrate MMOD protectionDemonstrate dust mitigation techniquesDemonstrate fire detection and suppressionDemo/test radiation shieldingDemonstrate closed loop life support systemsDemo closed laundry/hygieneDemo thermal protection from night/day extremes

Provide a safe and enduring habitatDemonstrate long-term remote health careUnderstand effects of the space env. on crew healthUnderstand impact of pres. and O2 conc. on healthDemonstrate In-Situ Science CapabilitiesDemonstrate curation and contamination control

1413121197654321 21201918171615

Demonstrate assembly of habitat elements

Demo surface communications capability

Demo mobility for unloading/moving elements

108

Demo long-dist, pressurized mobility capability

Demo long-distance surface navigation

Test equipment repair techniques

Demo ISRU excavation processesDemonstrate Solar Power SystemDemonstrate Nuclear Power SystemCryo Fluid Storage and Distribution

Demo a high performance EVA suitDemo sustained EVA schedulesDemo long-distance EVA NavigationDemonstrate suit durability/repair activitiesDemo high use airlock or suitlockDemo robots that supplement astronaut activitiesUnderstand MTBF of equipment

Demo commonality and scavenging of sparesDemo remote training systemsDemo teleoperations capabilitiesLearn how to best perform basic working tasksDemo production of ISRU ConsumablesDemo production of ISRU Propellant

Demonstrate MMOD protectionDemonstrate dust mitigation techniquesDemonstrate fire detection and suppressionDemo/test radiation shieldingDemonstrate closed loop life support systemsDemo closed laundry/hygieneDemo thermal protection from night/day extremes

Provide a safe and enduring habitatDemonstrate long-term remote health careUnderstand effects of the space env. on crew healthUnderstand impact of pres. and O2 conc. on healthDemonstrate In-Situ Science CapabilitiesDemonstrate curation and contamination control

14131211976543211807 14 28 85 180

Syst

ems

Lab

Crew DurationMission

Key Elements

- Crewed Mission- Cargo Mission

Objective 0% Satisfied

Objective 100% Satisfied

Objective 50% Satisfied

Campaign Extensibility Objective Satisfaction

Knowledge will continueto accrue after nominal objective is satisfied

180180 180 180

ISRU

Habi

tat

Mobi

lity

Healt

hRe

pair

Ops

EVA