constellation program overview · launch vehicle ares v - heavy lift launch vehicle ares i - crew...
TRANSCRIPT
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