Lunar Capability Concept Review (LCCR) - Lunar and Planetary

Lunar Capability Concept Review(LCCR)

June 18 – 20, 2008Report to the PSS

Transportation Systems Only

June 18 - 20, 2008 Section 00: LCCR Agenda Page 2June 18 - 20, 2008 Section 00: LCCR Agenda

LCCR AgendaDate Time Topic PresenterJune 18 8:00 – 8:15 am Welcome / Introduction Hanley / Muirhead

8:15 – 9:00 am 01: LCCR Overview Knotts9:00 – 9:15 am 02: Lunar Requirements Summary Knotts9:15 – 10:00 am 03: CxAT_Lunar Study Process Joosten10:00 – 11:00 am 04: LSS Concepts Culbert11:00 – 11:30 am Lunch11:30 am – 2:00 pm 05: Altair System Hansen / Connolly2:00 – 4:30 pm 06: Ares V System Creech4:30 – 5:30 pm 07: Ground Operations Quinn

June 19 8:00 – 8:30 pm 08: Ares V and Altair Margins Strategies and Basis Muirhead8:30 – 10:30 am 09: Integrated Performance and Mission Design Martinez10:30 am – 12:30 pm 10: Strategic Analysis Falker12:30 – 1:00 pm Lunch1:00 – 3:00 pm 11: HLR POD Architecture Drake3:00 – 5:00 pm 12: LCCR Product Summary and Forward Plan Parkinson5:00 – 5:30 pm 13: Architecture Summary and Next Steps Muirhead

June 20 8:00 – 9:00 am 14: MCR Wrap-up – Altair Hansen / Graham9:00 – 10:00 am 15: MCR Wrap-up – Ares V Creech10:00 – 10:30 am 16: LCCR Success Criteria Review Knotts10:30 – 11:00 am Summary / Conclusions Hanley11:00 – 11:30 am Board Discussion

Section 05: Altair SystemJune 18 - 20, 2008 Page 3Section 05: Altair SystemJune 18 - 20, 2008

Heavy LiftLaunch Vehicle

Crew Launch Vehicle

Earth DepartureStage

Crew Exploration Vehicle

LunarLander

Components of Program Constellation


Typical Lunar Reference Mission

Ascent StageExpended

ED

S, L

ande

r

CE

V

Earth DepartureStage Expended

Lander Performs LOI100 kmLow LunarOrbit

Vehicles are not to scale.

LowEarthOrbit

ServiceModuleExpended

MOON

EARTH

Direct EntryLand Landing

Section 03: CxAT_Lunar Study ProcessJune 18 - 20, 2008 Page 5Section 03: CxAT_Lunar Study ProcessJune 18 - 20, 2008

Background

VSEVSE

ESASESAS

GlobalGlobalExplorationExploration

StrategyStrategy

LAT1LAT1

LAT2LAT2CxATCxATLunarLunar

June 18 - 20, 2008 Section 01: LCCR Overview Page 6June 18 - 20, 2008 Section 01: LCCR Overview Page 6

LCCR Scope

♦LCCR will define a Point of Departure (POD)* transportationarchitecture for the CxP Lunar Capability includingcapabilities to:• Deliver and return crew to the surface of the moon for short durations,

i.e. Human Lunar Return (HLR)• Enable establishment of a lunar outpost

♦This review focuses on the conceptual designs and keydriving requirements for Ares V and Altair (crewed and cargo)

♦This review assumes the capabilities of Ares I and Orion forthe lunar missions

♦This review will show how the POD transportationarchitecture, including EVA and Ground Ops, supports arange of mission campaigns and possible surfacearchitecture solutions• Specific Lunar Surface Systems definition is not part of this review

*This is a POD transportation architecture and NOT the final baseline

June 18 - 20, 2008 Section 02: LCCR Requirements Summary Page 7June 18 - 20, 2008 Section 02: LCCR Requirements Summary

CxP L2 Lunar Design Reference Missions

• DRM 1 : Lunar Sortie Crew DRM− This mission lands anywhere on the Moon, uses only on-board consumables, and leaves within ~1 week.

This mission enables exploration of high-interest science sites, scouting of Lunar Outpost locations,technology development objectives, and the capability to perform EVAs.

• DRM 2 : Uncrewed Cargo Lander DRM− Used to support an Outpost, help build one, or merely preposition assets for a subsequent Sortie Lander,

this uncrewed mission lands anywhere on the Moon, and has enough resources to sustain itself until acomponent of the Lunar Surface Systems takes over.

• DRM 3 : Visiting Lunar Outpost Expedition DRM− Analogous to an assembly flight to ISS, this mission lands at the site of a complete Outpost or one under

construction, and allows crewmembers to extend their stay by using assets of the Outpost rather than onlywhat is carried onboard their Lander.

• DRM 4 : Resident Lunar Outpost Expedition DRM− Realizing one of the goals of US Space Policy, this mission allows a sustained human presence on the

surface of the Moon, since it follows a single crew of four to the surface, transitions them to a habitat at anOutpost, and gets them back to Earth after transitioning over to a replacement crew.

• DRM 5 : Outpost Remote DRM− This mission is separated in function from the other DRMs by focusing only on those Lunar Surface Systems

which need to operate without human intervention, either because humans are not present to operatethem, or the task is more easily performed in an autonomous or automatic manner.

Section 06: Ares V SystemJune 18 - 20, 2008 Page 8Section 06: Ares V SystemJune 18 - 20, 2008

Building on a Foundation of Proven Technologies- Launch Vehicle Comparisons -

Earth DepartureStage (EDS) (1 J–2X)234.5 t (517.0k lbm)LOX/LH2

Core Stage(5 RS–68B Engines)1,435.5 t(3,164.8k lbm)LOX/LH2

Crew

LunarLander

Altair

5-SegmentReusableSolid RocketBooster(RSRB)

Space ShuttleSpace Shuttle Ares IAres I Ares VAres V Saturn VSaturn V

2 5-SegmentRSRBs

Orion

DAC 2 TR 5

S-IVB(1 J–2 engine)108.9 t(240.0k lbm)LOX/LH2

S-II(5 J–2 engines)453.6 t(1,000.0k lbm)LOX/LH2

S-IC(5 F–1)1,769.0 t(3,900.0k lbm)LOX/RP-1

Height: 111 m (364 ft)Gross Liftoff Mass:

2,948.4 t (6,500.0k lbm)Payload Capability:

44.9 t (99.0k lbm) to TLI118.8 t (262.0k lbm) to LEO



63.6 t (140.2k lbm) to TLI (with Ares I)55.6 t (122.6k lbm) to Direct TLI

143.4 t (316.1k lbm) to LEO

Upper Stage(1 J–2X)137.1 t(302.2k lbm)LOX/LH2

Height: 99 m (325 ft)Gross Liftoff Mass:927.1 t (2,043.9k lbm)Payload Capability:

25.6 t (56.5k lbm)to LEO



25.0 t (55.1k lbm)to Low Earth Orbit (LEO)

Ove

rall

Vehi

cle

Hei

ght,

m (f

t)

122 m(400 ft)

91 m(300 ft)

61 m(200 ft)

30 m(100 ft)

0

PPBE Submit (51.0.39)

Section 03: CxAT_Lunar Study ProcessJune 18 - 20, 2008 Page 9Section 03: CxAT_Lunar Study ProcessJune 18 - 20, 2008 9

Ares V Trade Space

1.5 Launch TLI Capability

Core Booster

Standard CoreW/ 5 RS-68

Opt. Core Length /6 Core Engines

5 SegmentPBAN

Steel CaseReusable

5 SegmentHTPB

Composite CaseExpendable

5.5 SegmentPBAN

Steel CaseReusable

Spacers: 1

LCCR Initial Reference

-2.3 t

67.4 t

51.0.41

51.0.40

69.7 t

+6.1 t

51.0.39

63.6 t

+3.7 t

+5.0 t

+5.0 t 51.0.46

68.6 t

51.0.47

74.7 t

+6.1 t

Spacers: 1

51.0.48

71.1 t

-3.6 t Spacers: 0

Common DesignFeaturesComposite Dry Structuresfor Core Stage, EDS &Shroud

Metallic Cryo Tanks for CoreStage & EDS

RS-68B Performance:Isp = 414.2 secThrust = 797k lbf @ vac

J-2X Performance:Isp = 448.0 secThrust = 294k lbf @ vac

Shroud Dimensions:Barrel Dia. = 10 mUsable Dia. = 8.8 mBarrel Length = 9.7 m

Section 03: CxAT_Lunar Study ProcessJune 18 - 20, 2008 Page 10Section 03: CxAT_Lunar Study ProcessJune 18 - 20, 2008 10

Recommendations

♦ Approach• Applied Margins/Reserves

Methodology to Altair &Ares V (net loss ofarchitecture “performance”)

• Developed higher fidelitymission analysistechniques (net gain ofarchitecture “performance")

♦ Result• Lunar Architecture still

requires ~12% additionalperformance

• Higher performance Ares Voptions required

• Altair prop loading andloiter requirementsdetermined

Alta

ir W

et M

ass

Delta-V

CrewOptimized

CargoOptimized

Alta

ir W

et M

ass

Post-LOI Loiter Time


Recommended New Point of Departure- Vehicle 51.0.48 -

♦Vehicle 51.0.48 recommended• 6 Engine Core, 5.5 Segment PBAN Steel Case

Booster• Provides Architecture Closure with Margin

♦Recommend Maintaining Vehicle 51.0.47 withComposite HTPB Booster as Ares V Option• Final Decision on Ares V Booster at Constellation

Lunar SRR (2010)• Additional Performance Capability if needed for

Margin or requirements• Allows for competitive acquisition environment for

booster

♦Near Term Plan to Maintain Booster Options• Fund key technology areas: composite cases, HTPB

propellant characterization• Competitive Phase 1 Industry Studies

21.7 m

10 m

58.7 m

71.3 m

23.2 m

10 m

NOTE: These are MEAN numbers

116.2 m


Summary

♦Ares V Initial 2008 Capability (51.0.39) exceeds Saturn Capability by~30%

♦Ares V LCCR analysis focused on meeting lunar requirements anddeveloping margin

♦Ares V is sensitive to Loiter, Attitude, Power, and Altituderequirements in addition to payload performance

♦Recommended new POD Ares V can meet current HLRrequirements with ~6 t of Margin• Additional budget required (~$1.7BRY) for the 5.5 Segment PBAN Booster

and 6 Engine Core

• Plan to maintain new composite HTPB booster as an option

♦Additional analysis required to determine Ares V PLOM and PLOCcontributions for CARD recommendations


Altair Lunar Lander

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

♦ 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 hydrogenpropulsion

♦ Ascent stage:• Hypergolic Propellants or Liquid

oxygen/methane


Structures and Mechanisms

Propulsion

Thermal Control

Life Support

Other

Propellant

Non-Propellant Fluids

Manager's Reserve

Mass Available for PayloadAvionics Power

Configuration Variants

Outpost Variant45,000 kg

Descent ModuleAscent Module

Sortie Variant45,000 kg

Descent ModuleAscent Module

Airlock

Cargo Variant53,600 kg

Descent ModuleCargo on Upper Deck

Sortie Mission Lander


Design Approach

♦ Project examined the multitude of concepts developed in the post-ESAS era, tooklessons learned and began to develop a real design.

♦ Altair took a true risk informed design approach, starting with a minimumfunctionality design and adding from there to reduce risk.

♦ Lunar Design Analysis Cycle (LDAC) 1 developed a “minimum functional”vehicle.

• “Minimum Functionality” is a design philosophy that begins with a vehicle that will perform themission, and no more than that

• Does not consider contingencies• Does not have added redundancy (“single string” approach)• Provides early, critical insight into the overall viability of the end-to-end architecture• Provides a starting point to make informed cost/risk trades and consciously buy down risk• A “Minimum Functionality” vehicle is NOT a design that would ever be contemplated as a

“flyable” design!

♦ LDAC-2 determined the most significant contributors to loss of crew (LOC) andthe optimum cost/risk trades to reduce those risks.

♦ LDAC-3 (current LDAC) is assessing biggest contributors to loss of mission(LOM) and optimum cost/risk trades to reduce those risks.

♦ Goal of the design process is to do enough real design work to understand anddevelop the requirements for SRR.


LDAC-2 Overview

♦ The initial Lander Design and Analysis Cycles (May-November 2007) created a“minimal functionality” lander design that serves as a baseline upon which to addsafety, reliability and functionality back into the design with known changes toperformance, cost and risk.

♦ LDAC-2 completed in May 2008. Goal was to “buy down” Loss of Crew (LOC) risks.

♦ “Spent” approximately 1.3 t to buy down loss of crew (LOC) risks.

♦ “Spent” an additional 680kg on design maturity.

Events\Hazards Life SupportThermalPropulsionStructures and MechanismsPowerAvionics

Sum of System Contributions to LOC/Mass Available for Payload

0.0E+00

2.0E-02

4.0E-02

6.0E-02

8.0E-02

1.0E-01

1.2E-01

1.4E-01

1.6E-01

1.8E-01

LDAC-1 LDAC-2

P(LO

C)

0

500

1000

1500

2000

2500

3000

3500

4000

mas

s (k

g)1 in 206

1671 kg

500 kg minimum payload

3652 kg1 in 6

Mass Available for Payload

Individual Subsystem Contribution to LOC:


Launch Shroud

♦ Packaging the landerwithin the Ares V launchshroud is akin to building a“ship in a bottle”

♦ Ares V descent stagestructure and landing geardesigned to package withina 10 meter launch shroud(8.8 meter diameterdynamic envelope)

7-Apr-2008 NASA Internal Only Your Initials Here / 2

Migration of StructuralConfiguration to 10m Shroud

♦ Key features– Assumed 8.8m Dynamic Envelope (but not a hard number)– Scaled LDAC1 -Delta w/No Major Configuration Changes– Incorporated Updates for 10m Shroud & For Increased ΔV– Single CAD Update, Two Analysis Cases (10m & 10m + ΔV)– AL and AM Global Geometry Unchanged– Items that Did Change (or that were matured) Include

• resized propellant tanks, engine mounts• modified tank support scheme• added realistic clearances for plumbing, radiators, insulation, struts• Refined AM/DM separation and AM/AL separation/tunnel Details• Some hatch details• Descent stage is now “Clocked ” 45o with respect to AM• Deck Height = 5.9m (upgrade to 10m shroud) , 6.2m (shroud + ΔV)

♦ Mass impact– 10m Shroud Migration Adds +46 kg (DS Truss -44.3 kg, EDSA +90.6 kg)– Increased ΔV Adds +217 kg (+164.4 kg DS Truss, EDSA +52.67 kg) – +47 kg Due to Combination of both 10m Shroud & Increased ΔV– TOTAL MASS INCREASE: 310 kg

7-Apr-2008 NASA Internal Only Your Initials Here / 3

LDAC1-Delta & LDAC2 Configurations

LDAC1-Δ LDAC2

AirlockAM Tankswith RCSPlaceholderStructure

ModifiedCone Supports

9.5m9.5m

ModifiedHatch


Payload Shroud Current Design Concept

Quad Sector Design

Thrust Rail Vertical Separation SystemPayload umbilical separation

Frangible JointHorizontal Separation

• Composite sandwich construction (Carbon-Epoxy face sheets, Al honeycomb core)

• Painted cork TPS bonded to outer facesheet with RTV

• Payload access ports for maintenance,payload consumables and environmentalcontrol (while on ground)

Mass: 9.1 t (20.0k lbm)POD Geometry: BiconicDesign: Quad sectorBarrel Diameter: 10 m (33 ft)Barrel Length: 9.7 m (32 ft)Total Length: 22 m (72ft)

Point of Departure(Biconic)

Leading Candidate(Ogive)

Section 07: Ground OperationsJune 18 - 20, 2008 Page 19Section 07: Ground OperationsJune 18 - 20, 2008

Ares V Shroud Encapsulation Issues

♦Shroud quad sectorconfiguration will likelypreclude partialencapsulation in SSPF

♦Shroud Encapsulationrisks are the same forall 51 Series Ares Vvariants

♦GO and Ares V teamswill continue to studyshroud groundprocessingalternatives.

June 18 - 20, 2008 Section 09: Integrated Performance and Mission Design Page 20June 18 - 20, 2008 Section 09: Integrated Performance and Mission Design

Temporal Availability Contour Plots

♦ Temporal availability contour plots show the availability of lunar landing sites over the lunarnodal cycle.

♦ The following plots reflect both global sortie mission availability for the Altair alone as well asfor the integrated Orion/Altair mission.

♦ The following proposed ESAS landing sites are indicated in the contours:

Landing Site Latitude Longitude Notes-------------------------------------------------------------------------------------------------------------------------------------------A. South Pole 89.9 S 180 W (LAC 144) rim of ShackletonB. Far side SPA floor 54 S 162 W (LAC 133) near BoseC. Orientale basin floor 19 S 88 W (LAC 91) near KopffD. Oceanus Procellarum 3 S 43 W (LAC 75) inside Flamsteed PE. Mare Smythii 2.5 N 86.5 E (LAC 63) near PeekF. W/NW Tranquilitatis 8 N 21 E (LAC 60) north of AragoG. Rima Bode 13 N 3.9 W (LAC 59) near Bode vent systemH. Aristarchus plateau 26 N 49 W (LAC 39) north of Cobra HeadI. Central far side highlands 26 N 178 E (LAC 50) near DanteJ. North Pole 89.5 N 91 E (LAC 1) rim of Peary B


Global Access/LOI Δ-V/LLO loiter

♦ Access to all lunar landing sites (“global access”) requires acombination of additional LOI Δ-V, pre-descent LLO loiter, andpost-ascent LLO loiter• Minimum energy LLO maneuvers are sufficient for polar outpost missions

♦ Altair to size tanks for 1000 m/sec LOI maneuver, loadconsumables for 4 additional days of LLO loiter


Global Sortie Mission Sequence

GIVEN:EpochLanding Site LAT/LONGTLI Window DurationTrans-Lunar Time of FlightPost-LOI Extended LoiterPre-TEI Extended LoiterTrans-Earth Time of FlightEntry Interface Conditions

DETERMINE:Required Propellant Mass for EDS, Altair, andOrion Vehicles.

ACTIVE VEHICLES: 1. ORION ACTIVE 2. ALTAIR ACTIVE 3. EDS ACTIVE

TLI

3-7 DaySurface Stay

ASCENTTO DOCK

Earth-MoonTransfer

3-BurnLOI

3-BurnTEI

RENDEZVOUSIN LEO

Moon-EarthTransfer

EILOI-1

LOI-3

TEI-1 TEI-3TCM’s TCM’s

ASCENTPLANE

CHANGE

1-dayLoiter

1-dayLoiter

Post- LOIExtended

Loiter

Pre-TEIExtended

Loiter

LLO ORBIT MAINTENANCE

Landing Site Specified

DE-ORBITPDI

IC: Post-Ascent LEO

Epoch Specified


Greater Than Zero Temporal Coverage

♦ In order to ensure global lunar surfaceaccess, the following minimum missionarchitecture conditions were determinedto be sufficient for providing access toall lunar landing sites at some epochduring the lunar nodal cycle*:

• 48 HR LOI and TEI flight times• 5 days of extended LOI loiter• 3 days of extended TEI loiter

♦ For these conditions the Altair canprovide access to the worst caselanding sites ~8% of the time.

♦ For the integrated capability, thisprovides for access to the worst caseintegrated landing sites ~5% of the time.

1000 m/s LOI ΔV Capability

AltairOnly

IntegratedAltairand

Orion

* To the resolution of the MAPP data and given the assumptions in the MAPPanalysis (e.g., no Earth perturbations assumed in LOI and TEI 3-burn maneuvers).


LDAC-2 Configuration


Vehicle Architecture

DescentModule

AscentModule

Airlock♦ Three Primary Elements

• Descent Module− Provides propulsion for TCMs, LOI,

and powered descent− Provides power during lunar transit,

descent, and surface operations− Serves as platform for lunar landing

and liftoff of ascent module• Ascent Module

− Provides propulsion for ascent fromlunar surface after surface mission

− Provides habitable volume for fourduring descent, surface, and ascentoperations

− Contains cockpit and majority ofavionics

• Airlock− Accommodates two crew per

ingress / egress cycle− Connected to ascent module via

short tunnel− Remains with descent module on

lunar surface after ascent moduleliftoff


Altair LDAC-2 Sortie Vehicle Configuration

DM LH2 FuelTank (x4)

AM ConnectingStructure(Remains on DM)

Radiator(x2)

DM Main Engine

Landing Leg(x4) DM RCS Thruster

Pod (x4)

PressurantTank (x2)

LIDS

AM Oxidizer Tank (x2)

AM RCS ThrusterPod (x4)

Pressurant Tank (x2)

AM Fuel Tank (x2)Docking Window(x2)

AirlockEgressHatch

Star Tracker and Comm.Antenna (x2)

Forward FacingWindow (x2)

AM Main Engine

AM-AirlockConnectingStructure

Airlock

AvionicsPlatforms (x2)

Thermal Insulation

LOX Tank SupportCone (x4)

Life SupportOxygen Tank

RCS Tanks

Avionicsboxes (x2)

Problem: central location ofcapsule = bad visibility.


Altair Key Messages

♦ Current design demonstrates a lander design that closes withinthe Constellation transportation architecture

♦ Altair has investigated a wide breadth of lander concepts, usinglessons learned to influence the current design concept

♦ Altair has undertaken a process that begins with minimumfunctionality and buys back safety, reliability and additionalcapabilities with known performance, cost and risk impacts

♦ The Altair team is using this design process to help developgood requirements

♦ Design process (particularly risk based design approach) isresulting in a smart government design team

♦ Altair has used its bottoms-up design work to inform sizing oflanders for transportation architecture trades

♦ Altair has developed a detailed bottoms-up cost estimate


Sample Return Mass Considerations Nominal return mass: 100 kg. Note that Apollo 17 returned110.5 kg of sample.“The PSS views the sample mass allocation in the currentexploration architecture for geological sample return as too lowto support the top science objectives. We are asking thatCAPTEM undertake a study of this issue with specificrecommendations for sample return specifications.” Tempe Workshop, 2007.

CAPTEM: Minimum of 230 kg total return mass, but noted that CAPTEM: Minimum of 230 kg total return mass, but noted thaton the basis of simple extrapolation of the Apollo 17 mission,on the basis of simple extrapolation of the Apollo 17 mission,sample return mass could be as much as 800 kg.sample return mass could be as much as 800 kg. The recent Lunar Surface Scenarios workshop estimated The recent Lunar Surface Scenarios workshop estimatedthat a 7-day sortie mission with 4 crew and 8 that a 7-day sortie mission with 4 crew and 8 EVAsEVAs could couldcollect 306 kg of samples.collect 306 kg of samples.

100 kg IS NOT ENOUGH100 kg IS NOT ENOUGH


Sample Return Mass Considerations

LCCR Action Items:LCCR Action Items: Stochastic modeling of sample return mass Stochastic modeling of sample return masson the Altair ascent stage;on the Altair ascent stage; Study of Orion volume capacity for increasing Study of Orion volume capacity for increasingreturn sample mass.return sample mass.

At the moment there is 1.6 metric tons of At the moment there is 1.6 metric tons ofreserve mass on Altair, not including PMR.reserve mass on Altair, not including PMR.

June 18 - 20, 2008 Section 04: LSS Concepts Page 30June 18 - 20, 2008 Section 04: LSS Concepts

LCCR & The Surface Architecture(not part of this LCCR)

Can the Constellation transportation system(Ares, Orion & Altair) support the deploymentand operations of a lunar outpost?

Can

Is the POD cargocapacity to thelunar surface

enough?

Do the surfacesystems fit in the

Ares-5 shroud andon the Altair deck?

Have solutions forunloading cargo to

the surface beenidentified?

Logistics 2.331 1.640

Nitrogen 0.000 0.000

0.080

3.971Water 0.000 0.000 0.000

0.000

3.471

Oxygen 0.000 0.000 0.000

TotalPackagingCarriedCategory0.500Pressurized 0.420

Unpressurized 1.911 1.560

14.5514.600.05

CapabilityDifference

Total3.97

Science

OPS - ISRU system - H2 Reduction (0.5t) - TS3

0.69

Capabilitiy 14.60

6.130.850.160.24

14.60Baseline Capability

Lander Mass (t)

LogisticsExcavation - H2 Reduction (0.5t) - TS3 0.05

Logistics

Element Mass (t)

2 - Crew Mobility Chassis 2.13LCT (Lunar Communications Terminal) 0.32

Mobile Power UnitOTSE - Davit

2 - Pressurized Crew Cab

Yes Yes Yes


ISRU

Functional Description:Perform lunar regolith excavation andhandling, oxygen extraction fromregolith, and oxygen storage anddelivery, and support landerpropellant scavenging and waterproduction. For flexibility, two 1/2-scale plants will be delivered and 2sets of excavation tools.

• Total O2 Produced = 1000 kg/yr• Mass per O2 plant = 219 kg• Power per plant = 3.93 kW• Total Regolith = 415 kg/day• Excavation Tools = 42.7 kg(each)• Excavation Time = <1 hr/day

RESOLVESubscale O2Extraction andVolatile releasereactor

Oxygen Extraction from Regolith

Regolith Excavation and Movement

Excavation and O2 Plantmounted on mobile

chassis

TS 2/3 O2 Production Systemwith Storage and Thermal

Control

1 t of oxygen per year requires a regolith excavation rateof <1/2 cup per minute! (1% efficiency - 70% light)

Largehoppershold 1day’s

regolith

Radiator panelsfold down for

launch

Hoppersraised to

allowdumpingof spentregolith

into CMC

Scoop lifts11 kg regolith/scoop

(38 scoops to fillhoppers for day)

1st Gen O2 Production System(660 kg/yr ) for Field Demo, Nov. 08

Cratos Excavator

Area Clear Blade on CMC

Bucketwheel Excavator

O2 Storage

H2OProcessing

Regolith H2Processing


Surface Architectures AssessedThree surface architectures were developed in support of LCCR:

• Rapid Outpost Buildup (TS-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 (TS-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− Assumed water scavenging

• Initial Habitation Emphasis (TS-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− Assumed water scavenging

Surface Systems Review in 2010

June 18 - 20, 2008 Section 13: Architecture Summary and Next Steps Page 33June 18 - 20, 2008 Section 13: Architecture Summary and Next Steps

Lunar Transportation Architecture Recommendations

♦ Ares-V• Maximize commonality between Lunar and Initial Capabilities: Ares-V

51.0.48− 6 engine core, 5.5 segment PBAN steel case booster− Provides architecture closure with additional margin− High commonality with Ares I

• Continue to study the benefits/risk of improved performance: Ares-V51.0.47− Final decision on Ares V booster at Program SRR (6/2010)− Additional performance capability if needed for margin or requirements− Allows for competitive acquisition environment for booster− Requires further study and technology investment funding

♦ Altair• Provide a robust capability to support Lunar Outpost Missions:

− Optimize for crew missions (500 kg + airlock with crew)− Lander cargo delivery: ~ 14,500 kg in cargo only mode

• Size the system for global access while allowing future mission andsystem flexibility− Size Altair tanks for 1,000 m/s LOI delta-v− Size for an additional 4 days of Low-Lunar Orbit loiter (site specific)

• Retain adequate margins:− ~1,000 kg Program reserve at TLI− Minimum of 40% total Altair margin/reserve

♦ Orion• Continue to mature Orion vehicle concept• Maintain strong emphasis on mass control

− Continue to hold Orion control mass to 20,185 kg at TLI• Increase emphasis on evolution of Orion Block 2 to support lunar

Outpost missions

June 18 - 20, 2008 Section 13: Architecture Summary and Next Steps Page 34June 18 - 20, 2008 Section 13: Architecture Summary and Next Steps

DRMs/Mission Key Driving Requirements MappingLunar Sortie Design Reference Mission

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

<5.8d~4d

MOON

EARTH

LLO 100 km (54nm)

Direct or Skip Entry

ERO 241km(130nm)

905 t (2M lbm) 3,698 t (8.2 Mlbm)

1 - 5 d

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

1-5d

Water Landing

7 d

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

Altair• Crew of 2-4 + 500 kg (1,102 lbm) cargo• Global Access• Landing accuracy ≤100 m (328 ft) with 95%

accuracy (♦)• 373 (♦) hrs crew support• Airlock functionality• LOC ≤ 1 in 250 (♦)• LOM ≤ 1 in 75 (♦)

3-burn LOI1-4 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)EVA Mass Allocation 171.5 kg (378.0 lbm)FCE Mass Allocation 133.8 kg (295.0 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)• FCE & EVA Mass Allocation 675 kg (1,488 lbs)• Orion 382 kg (842) unpressurized cargo• 21.1 days crew support• LOC ≤ 1 in 200• LOM ≤ 1 in 50

1d

7 d

Multi-Mission Phase Requirements• Anytime Abort• LOC ≤ 1 in 100• LOM ≤ 1 in 20 Descent ΔV 2,030 m/s (6,660 ft/s)

LH2/LO2 descent engine restartable/throttleable

Ares V• 4 launches per year (6 launches per year)• Weather exclusive launch availability TBD• 2 5.5 sebment SRBs; 6 RS-68B• LOC ≤ 1 in 37,000• LOM (vehicle) ≤ 1 in 125

♦ A TBD or TBR is associated withthis requirement

Documents

Lunar Capability Concept Review (LCCR) - Lunar and Planetary