Lunar Architecture Team OVERVIEW - · PDF file · 2007-02-19Lunar Architecture Team Approach ... Thermal Protection 2009, 2020A, 2022B 40 9 mENVCH5 Environmental Characterization

Lunar Architecture TeamOVERVIEWLunar Architecture TeamOVERVIEW

Tony LavoieDecember 7, 2006

Tony LavoieDecember 7, 2006

What is the Lunar Architecture Study?

• Study Objectives– Define a series of lunar missions constituting NASA’s

Lunar campaign to fulfill the Lunar Exploration elements of the Visions for Space exploration • Multiple human and robotic missions

– Develop process for future Architecture updates

• Lunar Architecture Team (LAT) Charter– Develop a baseline architecture concept and establish a

periodic architecture refinement by December 6, 2006 • Baseline Architecture traced to Objectives• Concept of Operations• Exploration Architecture Requirements Document –

Level 1 Requirements• Functional Needs / Technology Analysis

Lunar Architecture Team Approach

Two Phase Process

• Phase I - Provide sufficient definition and supporting rationale for near term missions to enable commitment to these missions– Define campaign to 2025 (defined to 2030 for future awareness)– Concentrate on early robotics– Basis for discussions with International Partners

• Phase II – Iterate with International partners to optimize response and seek best resource leveraging– Continue to refine with Trades for key variables– Discuss/Collaborate/Negotiate with International Partners– Complete in July 2007

Lunar Architecture Team Approach

• Construct multi-program/center/Directorate Team (LAT)• Develop common set of Groundrules & Assumptions

– Later forms basis of top level requirements

• Develop architecture to meet Objectives of Interests!

• Develop Objective Set– Rate Global Objective set (from Synthesis Team)

for each Theme– Identify specific Objectives of

Interest (highly rated Objectives)– Review/iterate with NASA

leadership• Refine Objective Set

– Identify Objective Owners for each Objective of Interest

– Objective Owners develop and further specify Objectives in Sub-Objectives as appropriate

– Review/iterate with NASA leadership

Top 40 Objectives

35 Fully Addressed4 Partially Addressed1 Not Addressed

Lunar Architecture Objective Mapping

Overall LAT Rank LEAG Score (out of 10)

Objective ID Number Category Short Title Addressed During Completion Status Comments

1 10 mCAS2 Crew Activity Support EVA Suit 2020B

2 9 mLSH3 Life Support & Habitat Closed Loop ECLSS (physiochemical) 2022B

3 10 mEHM1 Environmental Hazard Mitigation

Radiation Shielding (Background & Solar Flares) 2022B

Further work required to identify how radiation shielding will be implemented on Lunar surface systems based on determination of

acceptable risk levels

4 10 mLSH1 Life Support & Habitat Habitation Systems 2020A, 2022B

5 9 mHH2 Human Health Lunar Environment Effects on Humans 2020A, 2022B

6 9 mOPS1 Operations, Test & Verification Human Surface Ops (Make EVA easier) 2020A, 2022B

7 9 mHH1 Human Health Fundamental Biological & Physiological Studies 2020A, 2022B

8 9 mOPS10 Operations, Test & Verification Lunar Repair Techniques 2020A, 2022B

9 9 mPWR1 Power Power Generation, Storage, & Distribution 2019B, 2020B, 2021A, 2021B, 2023A

10 8 mHH3 Human Health Lunar Health Care 2020A, 2022B

11 Not Ranked mPE2 Program Execution Exploration Strategy 2019B

12 10 mTRANS2 Transportation Autonomous Lander 2011, 2014, 2016, 2018, 2019B, 2020A

13 9 mEHM2 Environmental Hazard Mitigation Dust Mitigation Techniques 2014, 2020B, 2022B

14 9 mCAS3 Crew Activity Support Human Machine Partnership 2020B, 2021A, 2022B The phasing in of crew aids has not been implemented yet but there is sufficient room in the manifest to accommodate them

15 Not Ranked mPE6 Program Execution Affordability & Sustainability 2019B, 2025B

16 9 mOPS9 Operations, Test & Verification Crew-Centered Control 2020B, 2021A, 2022B, 2024A

17 9 mCOM1 Communications Scalable Communications 2019B, 2020A, 2022B

18 8 mHH4 Human Health Reduced Lunar Habitation Pressure Effects 2020A, 2022B

19 10 mLRU6 Lunar Resource Utilization Tools, Technologies, & Systems for ISRU 2011, 2014, 2016, 2018, 2021A

20 Not Ranked mOPS3 Operations, Test & Verification Mars Analog 2019B, 2020A, 2021A,

2022A, 2022B, 2023B, 2024B

Completely Addressed Partially Addressed Not Addressed

Lunar Architecture Objective Mapping (continued)

Overall LAT Rank LEAG Score (out of 10)

Objective ID Number Category Short Title Addressed During Completion Status Comments

21 9 mSM1 Surface Mobility Surface Mobility for Crew & Cargo 2014, 2019B, 2020A, 2022A

22 10 mLRU7 Lunar Resource Utilization Produce Propellants & Other Consumables 2014, 2016, 2018, 2021A

23 9 mLRU1 Lunar Resource Utilization Characterize Lunar Resource Potential 2009, 2011, 2012, 2014, 2016, 2018

24 10 mLRU3 Lunar Resource Utilization Demonstrate ISRU Technologies 2016, 2018, 2021A

25 Not Ranked mPE7 Program Execution Program Execution Flexibility 2025B

26 Not Ranked mPE3 Program Execution Maximize Synergy 2025B

27 9 mTRANS3 Transportation Cryo Fluid Management 2021A, 2021B, 2023A

27 9 mGEO8 Geology Characterize Potential Resources 2009, 2011, 2012, 2014

29 5 mOPS2 Operations, Test & Verification Remote Training 2020A, 2022B

30 10 mCAS5 Crew Activity Support Teleoperations & Telepresence 2014, 2018, 2019B, 2020A, 2021A, 2022B

31 Not Ranked mPE4 Program Execution Emphasize System Performance 2025B

32 9 mGEO7-1 Geology Characterize Lunar Volatiles 2008, 2012, 2014

33 8 mSM2 Surface Mobility Surface Mobility for Outpost 2022A

34 10 mENVMON1 Environmental Monitoring Monitor Space Weather 2019B, 2020A, 2022BCan partially addressed by instruments on the uncrewed landers and

surface habitats, but further work with the science community needed to identify what is required to fully address this objective

35 6 mCAS4 Crew Activity Support Autonomous Robotic Support for EVA & Long Range 2019B, 2025B Crew aids have not been manifested into this campaign at his time but

will be once refined needs are identified

36 3 mLRU9 Lunar Resource Utilization Lunar Elements that Use ISRU 2019B, 2020A, 2022B

37 9 mNAV1 Navigation GNC Lunar Capabilities 2019B, 2020A, 2022B

38 10 mENVCH3 Environmental Characterization Characterize Surface Radiation Environment 2011, 2014

39 9 mEHM4 Environmental Hazard Mitigation Thermal Protection 2009, 2020A, 2022B

40 9 mENVCH5 Environmental Characterization Characterize Dust Environment 2011, 2014 Further work required to identify how dust will affect and be mitigated

on Lunar surface systems

Completely Addressed Partially Addressed Not Addressed

Key Decisions: Sortie vs. Outpost

Courtesy Cornell University/Smithsonian Institution

South Pole

Bussey, et al, 1999

5 km

““WinterWinter”” Monthly Monthly IlluminationIllumination

>70%>70%>60%>60%>50%>50%

• First: What is the fundamental lunar approach?

• LAT concluded outpost first is best approach• Top 2 Themes – “Exploration Preparation”

and “Human Civilization” drive to outpost• Enables global partnerships• Allows development and maturation of ISRU• Results in quickest path toward other

destinations• Many science objectives can be satisfied at an

outpost

Overall Assessment

• 38 out of 69 rated objectives are GREEN (55%)

Integrated Assessment of Objectives

05

10152025303540

1 2 3 4 5

Evaluation Category

Num

ber o

f Obj

ectiv

es

1

2

3

4

5

1 Can be done at Outpost 2345 Cannot be done at Outpost

Can be done w/Robotics Partially done at Outpost Can be done at Outpost later

Outpost Site Location

Outpost Site: Polar• Safe

– Thermally Moderate• Cost Effective

– High percentage of sunlight– Allows use of solar power– Least Delta V required

• Resources– Enhanced hydrogen (possibly water)– Potentially other volatiles– Oxygen

• Flexibility– Allows incremental buildup using solar power– Enhanced surface daylight ops– One communication asset (with backup)– More opportunities to launch

• Exciting– Not as well knows as other areas– Offer unique, cold, dark craters

Data obtained during southern winter (maximum darkness)

Data obtained during northern summer (maximum sunlight)

South Pole

North Pole

Lunar Surface Temperature

110130150170190210230250270290310330350370

1 3 5 7 9 11 13 15 17 19 21 23 25 27 29

Time (Earth Days)

Tem

pera

ture

(K)

Equator45 deg75 deg88 deg

Lunar Surface Temperature Variation

‘The Lunar Base Handbook’ by Peter Eckart

Lunar Surface Temperature

110130150170190210230250270290310330350370

1 3 5 7 9 11 13 15 17 19 21 23 25 27 29

Time (Earth Days)

Tem

pera

ture

(K)

Equator45 deg75 deg88 deg

Shackleton Crater Rim with Notional Activity Zones

Iteration LoopIteration Loop

Lunar Architecture Development Process

Instructio

ns

Instructio

ns

Surface Mobility

Focus Elements

Power System

Science Capability

Habitation

Lander Design

Robotic Systems

ISRU

Comm/Nav

EVA

LAT is the bigger review group to “vet”instructions

Campaign Team (CT)• Campaign Team via

LAT instructs Focus Elements to craft the Elements. CT then integrates Elements into Lunar Campaign based on given boundaries and constraints

Objectives of Interest (with Sub-Objectives as appropriate)

Key Points: Lander Basic Architecture

Descent ModuleDescent Module

Ascent ModuleAscent Module

• Design Goals– Minimize Ascent

Module mass– Minimize

Descent Module mass

– Maximize landed “payload” mass

– Simplify interfaces

– Move functions across interfaces when it makes sense

• Design Goals– Minimize Ascent

Module mass– Minimize

Descent Module mass

– Maximize landed “payload” mass

– Simplify interfaces

– Move functions across interfaces when it makes sense

Landed Mass(Cargo, Habitat, Mobility, etc –

Maximized for Mass)

Landed Mass(Cargo, Habitat, Mobility, etc –

Maximized for Mass)

Point of Departure Only

Basic Tenets

• “Baseline” Outpost Buildup– Utilize only “downmass” cargo capacity of

piloted lander for incremental Outpost buildup

– Assume two piloted flights per year commencing in FY2020

• Alternate Outpost Buildup Strategies (not yet evaluated)– Swap cargo-only flights for crew

plus cargo flights

Ascent Module Cargo (Habitat) Cargo

Histogram of Cumulative Time on Surface

0

500

1000

1500

2000

2500

2018 2019 2020 2021 2022 2023 2024 2025 2026 2027 2028 2029 2030

Fiscal Year

w/Cargo Lander stretch

w/o Cargo Lander easy

w/Cargo Lander easy

Cum

ulat

ive

Day

s on

Lun

ar S

urfa

ce

180-Day MissionsCommence

Histogram of Cumulative Time on Surface

0

200

400

600

800

1000

1200

1400

1600

1800

2000

2018 2019 2020 2021 2022 2023 2024 2025 2026 2027 2028 2029 2030

Fiscal Year

Initial 180-Day Mission Capability

6000 kg surface capacity5000 kg surface capacity4000 kg surface capacityw/o Cargo Lander stretch

Human Lander Configuration

• Ascent module – Changed to LOX/Methane

(ISRU-compatible)• Descent module

– Composite structures– Capture residual fuel– Store fuel cell water for ascent

module thermal• Updated net payload mass

envelope• Updated Cost analysis• Initial lander configuration

Key Decisions: Power Systems

• Standard Power Unit (SPU) is a self contained, trailer-deployable unit with power generation, storage & distribution. Includes a deployable, Sun-tracking solar array, a regenerative fuel cell (RFC) subsystem with gaseous H2/O2 storage, and power distribution electronics and cabling.– Conservative interpretation of Digital Elevation Maps give 122 –

hr maximum eclipse

Solar ArrayRegenerablefuel cell and gas storage

Solar Standard Power Unit (SPU) Summary

System DescriptionStandard Power Unit (SPU) is a self contained, trailer-deployable unit with power generation, storage & distribution. Includes a deployable, Sun-tracking solar array, a Proton Exchange Membrane (PEM) regenerative fuel cell (RFC) subsystem with gaseous H2/O2 storage, and power distribution electronics and cabling. Make-up Power Unit (MPU) is a self contained RFC energy storage module deployed at a SPU unit.

The SPU2 initially delivers 10 kW of day time power and 2 kW of eclipse power to the outpost habitat element via a 200-m long power cable. In combination with 2 MPUs, the system delivers 6 kW continuous day/night power.

SPU SchematicDepending on the specific needs of the mission, the SPU2 is either deployed onboard the lander or unloaded from the lander and hauled by the unpressurized rover to be deployed elsewhere at the Outpost. Up to two MPU2 units work in conjunction with a single SPU2 and each adds an additional 2 kW of eclipse power capability. The MPU2 units must be in close proximity to the SPU2 in order to utilize power from the SPU2 solar array to recharge their RFCs. Additional daylight power is available from the SPU2 when the MPU2 RFCs are fully charged. The SPU2 includes a 200m spool of cable to carry power to various other elements, such as landers and habitats.

Deployment / Conops

SPUMPU

Key Points: Habitat – Classifications

CLASS IPre-integrated

CLASS IIPre-Fabricated orSpace/Surface -Assembled

CLASS IIIIn-Situ Derived and Assembled


Key Points: Habitat –Integration with Other Functional Elements

•Suit recharge, donning and doffing, regolith mitigation

•Interface with any deployed power and thermal rejection

•No interface •Landing aids, crew comm and telemetry

•Structural, possibly with self-leveling capability

•No interface, unless for direct crew transfer to pressurized rover

•Suit recharge, some maintenance,don/doff, and long term regolith mitigation

•Larger power system & deployable thermal rejection create additional infrastructure

•Reduce power levels during dormancy

•Common ISRU and Earth resupply interfaces to allow ECLSS use of In Situ resources

•Proximity landing aids for multiple elements

•Crew comm and comm for multiple surface elements

•Telemetry for more systems and health monitoring

•Deploy habitat and other surface elements

•Cargo resupply

•Transit crew to/from ascent vehicle and cargo from resupply

•Transportation between local surface elements

•May connect interfaces to other surface elements

Plus increased maintenance and repair for longer missions

•Larger power and thermal rejection system with more complex distribution in multiple elements

•Greater dependence on ISRU for consumables such as oxygen

•Plus increased comm with ground science and training

•Comm for increased family and medical video conference

•Deploy multiple volumes and layout base elements to interface with each other

•Cargo resupply

Plus•Increased cargo

•Maintain rovers•Possible transit to spoke locations

EVAPower &Thermal ISRU Nav/Comm Lander

MobilitySystems

14 day 14 day –– 6 month 6 month staysstays

>6 month stays>6 month stays

0-14 day stays


Habitation: Strategy Illustration

HAB 1Crew OperationsIncludes Basic Crew Accommodations (first initial element)• Sleeping• Eating• Hygiene• Stowage

HAB 2EVA Operations• Includes Additional EVA Capability• Redundant Airlock • Suit Maintenance• Spares Stowage• Suit Stowage

HAB 3Logistics/Resupply Operations• Includes Enhanced Accommodations for

180 days• Closed Loop Life Support System Hardware• Consumables Stowage for 180 increment• Spares Stowage (Supportability)• Interconnect Multiple Elements• Standard Docking Port for Resupply

HAB 4Mission/Science OperationsIncludes Enhanced Outpost Autonomy• IVA Glovebox• Life Science• EVA Tools Stowage

Conceptual Only!

Extravehicular Activity (EVA)

• General– EVA is a critical capability to support and enable Operations at a Lunar Outpost– On Outpost Missions, 2 crewmembers out on 8 hour EVA 5 days a week

• Pressure Garment– Single garment per crewmember per increment– Pressure garment provides thermal protection, regolith

mitigation, possibly limited radiation protection– PG will likely be a hybrid of common and custom sized

components until an adequate “fleet” is on hand to accommodate all crewmembers

– Pressure garment is maintainable on the lunar surface• Portable Life Support System (PLSS)

– Separate backpack, similar to Apollo approach– PLSS maintainable on the lunar surface– Major trade for next phase will be to study the design to determine best mix of

EVA and other external Lunar surface operations– PLSS can be recharged on rovers, so crewmembers generally egress the rover

with a full backpack– Backpack will provide advanced EVA time/consumables/location management to

crewmember

Key Points: Surface Mobility

• 4 basic mobility elements examined in depth– Unpressurized rover– Pressurized rover– Something to move large payloads

• Surface Mobility Carrier OR• Whole Lander Transport

– Crew Aids

• Trades still to be performed– Pressurized rovers vs mobile lander or mobile habitat

• Only relevant if some or all habitats (or whole landers) have built in mobility– Surface Mobility Carrier vs Whole Lander Transport

• Device capable of moving up to 6MT of payload or a device that moves the whole lander


Surface Mobility Assumptions & Constraints

• Potential capability buildup– 2020 – 2 Un-pressurized rovers, 2 to 4 crew, at least 50km range– 2021 – Capability to move large components (6 mT to 20 mT) at least 500m during 1

EVA time period– 2022 – Crew aids and pack-mule (multiple devices)– 2025 to 2027 – One pressurized rover – 2 crew, 500km round trip capability

• Assumptions– Unpressurized rovers able to perform work without

humans on the surface– Habitation Module and other movable payloads mass

less than 6 Metric tons – Many capabilities developed for unpressurized rover

can be reused on other mobility systems (Navigation sensors, Command & control, etc.)

– Smaller mobility systems can share common chassis/drive system with ISRU mobility platforms

– All mobility systems designed to last at least 5 years or longer on the surface of the moon


C&N Focus Element Summary – Robotic Phase

Lunar Relay Satellite 1 (LRS1):Early support for users beyond line of sight to Earth. Partial coverage over rest of Moon.

Provides >60% coverage

100m Nav accuracy during Descent & Landing

OverviewC&N services are provided by Earth-based Direct To Earth (DTE) antennas and a small S-band relay to support surface assets with limited or no Earth visibility.

Concept of OperationsLRS1 is launched prior to need for checkout & positioning to cover the crater rover. The Robotic Lander has redundant support for TT&C using DTE & LRS1 services. LRS1 provides basic services at medium data rates:

Trunk to Earth

S-band Relay to Users

S-band DTE to Users when in view

• Forward command• Return mission data &

telemetry• 1 & 2-way ranging &

Doppler tracking • Time dissemination


C&N Focus Element Summary – Crewed Phase

Lunar Relay Satellite 2 (LRS 2): Full C&N support to Outpost and partial coverage over rest of Moon.

100m Nav accuracy during Descent & Landing

OverviewC&N services are provided via DTE and relay plus a surface Lunar Comm Terminal (LCT) for the outpost.

Concept of OperationsThere is redundant comm to Earth:

For nominal surface operations, Outpost vicinity data is routed through the LCT to other lunar users or to Earth via DTS or LRS. LRS2 provides high capacity links. The LRS and LCT provide these services:

Ka & S-band to Users

Trunk to Earth

• LRS1 services plus• High rate data to Moon• Multiplex surface user data• Surface Nav Beacons Ka & S-band DTE

to Users when in view

LCT provides Outpost Wide Area Network

• Short missions via DTE and 1 relay• Extended missions via DTE & 2 relays.

Key Points: In-Situ Resources Utilization (ISRU)

• ISRU is a critical capability and key implementation of the VSE

• ISRU is also unproven

• Therefore, ISRU is manifested to take incremental steps toward the desired endstate

• Architecture takes advantage of ISRU from: LSAM residuals, ECLSS by-products, Lunar ISRU


ISRU Capabilities for Human Lunar Exploration

Pre-Outpost• Determine type, amount, and location of possible resources of interest (i.e. ilmenite, water,

etc.) – link to Science objectives if possible• Perform proof-of-concept and risk reduction demonstrations to certify ISRU capabilities for

use at the Outpost - link to commercialization of space if possible• Perform site characterization of topography, subsurface, and lighting conditions

Initial ISRU Capabilities to be pursued during early Outpost(first 5 years)• Pilot-scale oxygen production, storage, & transfer capability (replenish consumables)• Pilot-scale water production, storage, & transfer capability – assuming hydrogen

source/water is accessible• Demonstration of In-situ fabrication and repair demonstration• Possible ISRU Capability under evaluation - Excavation & site preparation (i.e. radiation

shielding for habitats, landing plume berms, landing area clearance, hole or trench for habitat or nuclear reactor, etc.)

Mid-Term ISRU Capabilities - Exploration growth• Propellant production for LSAM• Consumables for Pressurized rover or Hopper from Outpost• Nitrogen demonstration (if accessible and available)• Construction and fabrication demonstrations

Possible Long-Term Lunar Capabilities• In-situ manufacturing and assembly of complex parts and equipment• Habitat and infrastructure construction (surface & subsurface)• In-situ life support – bio support (soil, fertilizers, etc.)• Power generation for Moon and beyond: beaming, etc.

ISRU Analogies

Volume equivalent to 1 Metric Ton of

lunar regolith

Volume equivalent to 20 Metric Tons of lunar regolith

0.85 m

0.85 m

0.85 m

10 MT of oxygen per year requires a regolith excavation rate of ~1 cup per minute! (5% efficiency - 50% daylight)

~4 cups per minute! (1% efficiency - 70% light)

Houston Skyline

35 degree slope

15 degree slope

22 km diameter at rim2 km deep

Model of Dawes Crater (Shackelton analog)

300 MT of oxygen per year requires a regolith excavation rate of ~10 cups per minute! (14% efficiency - 70% time-polar region)

110 m

65 m10 MT of oxygen per year requires excavation of a soccer field to a depth of 0.6 to 8 cm!(1% & 14% efficiencies)

(worst case)

Lunar Robotic Exploration Architecture

Robotic Precursor Missions• Landing Site Recon• Reduce the risk for human missions• Potential for ISRU demonstrations• Scientific Exploration• Early and sustained public engagement

Implementation• LRO/LCROSS (launching in 2008)• Medium Lander at potential Outpost site

(Launching in 2011 or 2012)• SmallSat for communications demo

(Launching in 2011 or 2012) • Other mission opportunities afterwards for:

– Human Mission Risk reduction– Resource determination (especially Hydrogen and other volatiles)– ISRU proof of concept/risk reduction (O2, H2, H2O, N2, structure

fabrication, etc)– Science

INSTRUMENT Key Data Products

Exploration Benefits

Science Benefits

CRaTERCosmic Ray Telescope for the Effects ofRadiation

Lunar and deep space radiation environment and tissue equivalent plastic

response to radiation

500 m scale maps of surface temperature,

albedo, rock abundance, and ice stability

Maps of frosts and landforms in permanently

shadowed regions (PSRs).

Maps of hydrogen in upper 1 m of Moon at 10

km scales, neutron albedo

~25 m scale polar topography at < 10 cm

vertical, global topography, surface

slopes and roughness

LROCLunarReconnaissance Orbiter Camera

1000’s of 50cm/pixel images, and entire Moon at 100m in UV, Visible.

Illumination conditions of the poles.

Surface landing hazards and some resource

identification including locations of near constant

solar illumination

Tectonic, impact and volcanic processes, resource

evaluation, and crustal evolution

X and S-band radar imaging and

interferometry

Safe, lighter weight space vehicles. Radiation

environment for human presence at the Moon and

journeys to Mars and beyond.

Radiation boundary

conditions for biological

response . Map radiation reflected from lunar surface

DLREDiviner Lunar RadiometerExperiment

Measures thermal environment in permanent

shadow and permanent light, ice depth map

LAMPLymanAlpha MappingProject

Locate potential water-ice on the surface, image

shadowed areas, and map potential landing areas in

PSRs

LENDLunar Exploration Neutron Detector

Locate potential water-ice in lunar soil or

concentrations of implanted hydrogen

Source, history, migration and

deposition of polar volatiles

LOLALunarOrbiter LaserAltimeter

Identify safe landing sites, image shadowed regions, map potential surface ice, improve gravity field model

Global topography and gravity for

interior structure and geological

evolution

Mini-RFTechnologyDemonstration

Demonstrate new lightweight SAR and

communication technologies, locate potential water-ice

Source, history, deposition of polar

volatiles

LPRP-1 The Lunar Reconnaissance Orbiter

• Launch in late 2008 on a EELV into a direct insertion trajectory to the moon.

• On-board propulsion system used to capture at the moon, insert into and maintain 50 km mean altitude circular polar reconnaissance orbit.

• 1 year mission with extended mission options.

• Orbiter is a 3-axis stabilized, nadir pointed spacecraft designed to operate continuously during the primary mission.

• Investigation data products delivered to Planetary Data Systems (PDS) within 6 months of primary mission completion.

X

ZYLEND

LAMP

CRaTER

Mini-RF

DRLE

LOLA

LROC

LRO Mission Overview LRO Instrument Suite is a Robust Responseto Exploration Requirements

LCROSS Mission Overview

1 Earth Departure Upper Stage

Ecliptic North

Moon’s Orbit

• The LCROSS Mission is a Lunar Kinetic Impactor employed to reveal the presence & nature of water ice on the Moon– LCROSS Shepherding S/C (S-S/C) directs the 2000[kg]

(4410[lb]) EDUS1 into a permanently-shadowed crater at 2.5[km/s] (1.56 [miles/s])

– ~200 metric tons (220 tons) minimum of regolith will be excavated, leaving a crater the size of ~1/3 of a football field, ~15 feet deep.

– The S-S/C decelerates, observing the EDUS plume, and then enters the plume using several instruments looking for water

– The S-S/C itself then becomes a 700[kg] (1,543[lb]) 'impactor' as well

– Lunar-orbital and Earth-based assets will also be able to study both plumes, (which may include LRO, Chandrayaan-1, HST, etc)

Element Summary – Common Lander

Concept of OperationsThe Lander is placed into a TLI orbit by an EELV. A Star SRM provides the breaking burn for a direct landing trajectory with the on-board liquid propulsion system controlling terminal descent and landing. Precision navigation and hazard avoidance uses a combination of passive and active sensors evolving over time to demonstrate the ALHAT sensor compliment. There are two primary mission scenarios

OverviewThe common Lander is designed to support all Robotic missions with minimal modifications. The Lander has a mission specific “payload” capability of roughly 500kg. Propulsion is a combination of a solid rocket motor and a throttleable hypergolic bi-prop system. Power is provided by solar arrays. The Lander can land within 100m 3σ of a predetermined surface feature and avoid harmful hazards. The concept depicted is a Rim mission configuration.

• 1- Land at an illuminated location and perform fixed measurements over an extended period of time.

• 2-Land and deploy a 500 kg rover in a dark or illuminated area. Launch mass is roughly a little more than 4000 kg

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Unpressurized Rover

Crew/Cargo Lander

Solar Power Unit

Point of Departure Only – Not to Scale

Key Points: Outpost Build up

Year 0

Year 0









KEY

Solar Power UnitQuickTime™ and aTIFF (Uncompressed) decompress








Crew/Cargo Lander

Unpressurized Rover



Year 1-A7-Days

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Surface Mobility Carrier

KEY

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Crew/Cargo Lander

Unpressurized Rover



Year 1-B7-Days

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KEY

Solar Power Unit










Crew/Cargo Lander

Unpressurized Rover

Habitation



Year 2-A7-Days

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KEY

Habitation

Solar Power Unit










Crew/Cargo Lander

Unpressurized Rover

Power Storage Unit



Year 2-B7-Days

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Year 3-A

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Crew/Cargo Lander

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Year 3-B

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In-Sutu Resources Utilization (ISRU) Module

Logistics

KEY

Habitation

Solar Power Unit


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Crew/Cargo Lander

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Year 4

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Logistics

Crew/Cargo Lander

Unpressurized Rover


Year 5-B Starts 6 month incrementsYear 5-B Starts 6 month increments


Year 5-A

30-Days

Year 5-A

30-Days

Forward Work (January – July 07)

• Develop global view and mature architecture• Coordinate lunar exploration

plans among international and commercial partners and continueto look for other collaboration opportunities

• Refine campaign and architecture concepts and also element hardware concepts

• Update and baseline ESMD Requirements

• Develop Mars Reference Mission• Continue to engage academia, the private

sector, and other stakeholders in defining a sustainable program of exploration

Using current architecture as a point of departure

Documents

Lunar Architecture Team OVERVIEW - · PDF file · 2007-02-19Lunar Architecture Team Approach ... Thermal Protection 2009, 2020A, 2022B 40 9 mENVCH5 Environmental Characterization