Andrews Highlights

Reference concepts derived

from stakeholder objectives,

historical data, and timing /

sequence constraints.

7 Design Reference Cases

Key Aspects of DRC1

• Global access

• Launch anytime

• Landing location determined fromrobotics

• Nominal crew of 4

• Surface excursions of 10 days

• Lunar base grows for 1-year toursof duty (up to 8 crew)

• Commercial opportunity potentialafter 2020

LEO

LLOLMO

2010 - 2015

Lunar Com

Satellites

ISS CEVISS CEVISS CEV

L1

= Commercial Missions

= NASA Missions

= Military Missions

= Commercial Missions

= NASA Missions

= Military Missions

= Commercial Missions

= NASA Missions

= Military Missions

OTV is used to place NavCom satellites &

robotic precursors

Deep Space

Robots (JIMO)

launched from

L1 Gateway

Deep Space

Robots (JIMO)

launched from

L1 Gateway

ISSISS

ORSORSShuttle

(to 2013)

Cargo /

Logistics

(U/PLC)

Cargo /

Logistics

(U/PLC)

Commercial

Free Flyer @ 30

deg. (U/PLCC)

Commercial

Free Flyer @ 30

deg. (U/PLCC)

Mars Com

Satellites

Mars Com

Satellites

Mars Com

Satellites

Solar Power

LEO-L1 Tug

(LLT)CEV &

OTV

LTH Node

(CSM Derived)

L1 Cargo / Logistics

for LLT Pickup

Solar Power

LEO-L1 Tug

(LLT)

Solar Power

LEO-L1 Tug

(LLT)CEV &

OTV

LTH Node

(CSM Derived)

L1 Cargo / Logistics

for LLT Pickup

CEV &

OTV

CEV &

OTV

LTH Node

(CSM Derived)

LTH Node

(CSM Derived)

L1 Cargo / Logistics

for LLT Pickup

L1 Cargo / Logistics

for LLT Pickup

OTV is used to place

NavCom satellites &

robotic spacecraft

LSN &

ISRU

CPL

LSN &

ISRU

CPLCPL

RCB

EUS

ECB

EUS

ECB

All elements

limited to 15T

and 5x10m

LEO

LLOLMO

2010 - 2015

Lunar Com

Satellites

ISS CEVISS CEVISS CEV

L1

= Commercial Missions

= NASA Missions

= Military Missions

= Commercial Missions

= NASA Missions

= Military Missions

= Commercial Missions

= NASA Missions

= Military Missions

OTV is used to place NavCom satellites &

robotic precursors

Deep Space

Robots (JIMO)

launched from

L1 Gateway

Deep Space

Robots (JIMO)

launched from

L1 Gateway

ISSISS

ORSORSShuttle

(to 2013)

Cargo /

Logistics

(U/PLC)

Cargo /

Logistics

(U/PLC)

Commercial

Free Flyer @ 30

deg. (U/PLCC)

Commercial

Free Flyer @ 30

deg. (U/PLCC)

Mars Com

Satellites

Mars Com

Satellites

Mars Com

Satellites

Solar Power

LEO-L1 Tug

(LLT)CEV &

OTV

LTH Node

(CSM Derived)

L1 Cargo / Logistics

for LLT Pickup

Solar Power

LEO-L1 Tug

(LLT)

Solar Power

LEO-L1 Tug

(LLT)CEV &

OTV

LTH Node

(CSM Derived)

L1 Cargo / Logistics

for LLT Pickup

CEV &

OTV

CEV &

OTV

LTH Node

(CSM Derived)

LTH Node

(CSM Derived)

L1 Cargo / Logistics

for LLT Pickup

L1 Cargo / Logistics

for LLT Pickup

OTV is used to place

NavCom satellites &

robotic spacecraft

LSN &

ISRU

CPL

LSN &

ISRU

CPLCPL

RCB

EUS

ECB

EUS

ECB

All elements

limited to 15T

and 5x10m

9.3 12.8 12.8 12.8 11.0 9.7 11.0

44.3

64.9 64.9 64.960.2

46.653.6

9.3

12.8 12.8 12.8

11.0

9.7

11.0

44.3

64.9 64.9 64.9

60.2

46.6

53.6

7.6

9.6 9.6 9.6

8.6

5.6

6.528.3

38.4 38.4 38.4

35.6

15.3

21.910.1

10.9 10.9 10.9

10.9

11.5

13.3

6.7

6.7 6.7 6.7

6.7

6.7

6.7

4.5 4.5 4.5

4.5

4.1

4.5

4.5

0

50

100

150

200

250

Goal Baseline Trade Baseline SDLV Common LV's Dry Launch LLO Rendezvous Partial LLO

Rendezvous

Mass (

MT

)

Trade Results show masses needed in LEO for various cases

MM

CM

SM Gross

LM Prop

LM Dry

ETS Prop

ETS Dry

ETS Prop

ETS Dry

225.5 225.5

208.7

155.8

182.1

225.5

Note: Does not include polar

orbit with anytime abort

164.4

Boeing Highlights

Architecture driven from the Vision,

lunar exploration objectives, lunar

resource utilization, and national

security

Numerous architecture / design

trades

Architecture Summary

• Earth-Moon L1 Rendezvous

• LEO aggregation of elements

• Reusable lunar module

• Single stage LM

• Anytime returns; L1 gateway

• Trip time extended by L1 operations

• 14 days - continuous/long duration lunar

stays

Launch

Vehicle Options

Launch

Vehicle Options

South Pole SiteSouth Pole Site

Equatorial SiteEquatorial Site

Spiral 1

Spiral 2 & 3

Spiral 4 & 5

Mars Site

For crew returnfrom Mars

L1

L2

Baseline architecture provides extensible capability

for future exploration & supports future ventures

Assumption & Ground rules

- Lunar polar water ice may be accessible

- Necessary technologies at TRL 6 by

PDR

- Two launch providers

- ETO capability limited to 20/45+ MT LV

0

20

40

60

80

100

0

20

40

60

80

100

No

rmalized

Co

st

for

5 M

issio

ns

(% o

f m

axim

um

)

2-Stage

expendable LSAM

LLO rendezvous

(POD)

2-Stage

expendable LSAM

L1 rendezvous

1-Stage

reusable LSAM

LLO rendezvous

1-Stage

reusable LSAM

L1 rendezvous

22

314 Isp (Storables) in TEI and LSAM

363 Isp (LOX/CH4) in TEI and LSAM

454 Isp (LOX/LH2) in TEI and LSAM

11

Lockheed Martin Highlights

Guiding Principals

• Simultaneously address all Vision Objectives

• Start with Mars and work backwards

• Answer fundamental questions to determine post-

2025 future of exploration on Moon, Mars, Beyond

Numerous trades being conducted

Exploration Approach

• Mars robotic precursors (orbiters and landers)

already leading the way

– Pursuing water/life clues

– Providing global access to H20 ice at poles/near poles

– Soon to be performing combined science, ISRU,

engineering testbed missions

– Improving rover duration and speed

• Human missions likely to use fixed, near-equatorial

site for surface stays of 30-630 days

– Near the most desirable sites

– Low altitude to minimize entry/descent/landing difficulty

– Enables incremental build-up

– Most energy/mass efficient location

– More favorable thermal environment (20°C to -140°C)

– Safest approach

– Best solar fluence

POD Lunar Architecture Features (2018 -2023)

Remote operations

as warranted (e.g,

robotic H2O pilot at

southern pole if ice

is found)

Solar Flare/

Warning

System(s)

Sun

Direct Earth re-entry

and water recovery

operations

Consolidated

Mission Control

Earth

• Fixed Outpost

(pre-positioned and

incrementally built-up)

• Equatorial (+/-30°) focus

for lunar testbed, ISRU,

and science

– Crewed remote

landings elsewhere

as warranted

• Central location for

surface safe haven and

mission abort

• Global access via

human/robotic surface

transportation

(e.g., rovers, hoppers)

Moon

Equatorial

Outpost

Equatorial

Outpost

Crew field work

Ground processing

(crew, samples, systems)

ETR launch operations

• Cargo-only missions (Two 70mT)

• Crew missions (Two 70mT or 70mT

combined with single stick)

LEO automated rendezvous

and assembly

Low Lunar Orbit (LLO)

CEV/LSAM staging

Upgraded DSN

Communications

TBD on-orbit CEV/LSAM lifeboats for anytime rescue

Communications via

direct near-side broadband +

global narrowband TC&C

minisats

Reconnaissance Orbiters (e.g, LRO)

Surface Science (e.g.,

geoscience networks)Sample returns (e.g,

Moonrise @ Aitken Basin)

Roving robotic explorers

Astronomical observatory

proof of concepts

Northrop Grumman Highlights

Guiding Principles

• Simultaneously address each of the VisionObjectives

• Start with Mars and work backwards

• Answer the fundamental questions todetermine the post-2025 future ofexploration on Moon, Mars, and Beyond

Numerous trades being conducted

Exploration Approach

• Polar landing site

• 180 days surface duration

• Safe-haven abort; Implicit Rescue withResponsiveness

• 0-4 crew members

Mars preparation has two

components

• Technology demonstration and test

• Operational experience: “LessonsLearned”

EML1

Parallel

LLO

Stacked

ETS-2s Transport CEV/ASDS

in Parallel to L1ASDS Transports

HM to Moon

ETS-2/SM/RM

Station Keep

AS Transports

HM to L1

ETS-2 Transports CEV

to Direct Earth Insertion

AS

Transports

HM to LLO

CEV/AS in LLO

CEV Transports from LLO to

Earth Insertion

AS Discarded

SM/HM Earth De -Orbit

RM Return

ETS -2s Transport CEV/ASDS Stacked to LLO

EML1

ETS -2 Earth

De-Orbit

RM Return

ETS-2/SM/HM

Earth De -Orbit

ETS-2 Earth De -Orbit

CEV/ASDS in LLO

SM/RM in

LLO

ASDS Transports

HM to MoonETS-2

Discarded

Anytime Return Capabilities

LLO-A LLO- B LLO- C LLO- D LLO-E LLO-F LLO- G L1

IM

LE

O (

kg

) HM

RM

SM

AS

DS

ETS-A

ETS-B

CEV: Polar Orbit

Base: 70 degAPC: 560 m/sTEI: 1387 m/s

CEV: Polar Orbit

Base: 56 degAPC: 942 m/s

TEI: 1387 m/s

APC=Ascent Plane Change CEV: Polar Orbit

Base: 43 degAPC: 1285 m/sTEI: 1387 m/s

CEV: EquatorialBase: 0 deg

APC: 0 m/sTEI: 987 m/s

CEV: L1Base: Any

APC: 0 m/sTEI: 677 m/s

APC onCEV SM

APC on

LM AS

APC on

CEV SM

APC onLM AS

APC on

CEV SM

APC onLM AS

CTS-103

CTS-101-02

Orbital Sciences Highlights

Vision Mapped to Objectives, Missions,

Functions, and Requirements

Numerous trades being conducted

Example Habitation Alternatives

• Multiple Outpost Capability Anywhere on LunarSurface?

• Lunar Logistics Base: Establish Single LunarBase and Provide for Distributed ExplorationCapability?

• Lunar Orbiter: Provide 90 Day Capable LunarOrbiter With Surface Excursion CapabilityAnywhere on Lunar Surface?

Observations

• Coupling of Lunar Base Selection and LunarAbort/Safe Haven Capability

• It’s Primarily a Transportation and LogisticsProblem

• Lunar/Mars Operations Need to Be Compatibleand Traceable

• Need a Budget Strategy at Spiral Transitions toEnsure Sustainability

Raytheon Highlights

Vision for Space Exploration drives

exploration strategy

• Common infrastructure elements acrossmissions

• Not dependent on changes to political viability ofa single mission

Numerous trades being conducted

• Mission architecture related

• System sensitivities

• Technologies

Applicability of Lunar Operations

to Mars Exploration Identified

Key Architectural Construct

• Initial basing at South Pole

• Low-Lunar Orbit staging for cargo

• L1 staging for crew

• Lunar regolith used for crew protection from lunarenvironment

• Launch vehicle strategy being traded

• 3 crew members provide the operational andsafety margins desirable at minimum cost

• Critical technologies identified

SAIC Highlights

Study Status

• Preliminary analysis of Initial Concept for

Technical Solution (ICTS) 20-mission campaign

is complete

• Conservative assumptions have been made

throughout this preliminary analysis

• Results indicate that the baseline campaign is

both feasible and achievable

• Additional trade studies are underway

Campaign Studies Conducted

• Mass Flow

• Loss of Mission / Loss of Crew

• Risk Mitigation Measure

• Launch Manifest Trades

Figures of Merit Assessments

• Safety & Mission Success: LOM & LOC risks

have been identified and initial values generated

• Effectiveness: Being explored

• Extensibility: Campaign is based around

developing long-duration mission capability

without resupply (in preparation for Mars surface

missions) and selected subsystems

• Affordability: Under development

Draper / MIT Highlights

Stakeholder Value Analysis Approach:

• Stakeholders identified (14)

• Stakeholder needs defined (~90)

• Exploration objectives (24)

• Technical architecture proximate measures (~18)

• Indicator metrics (~40)

Mars Back Emphasis

QFD Tool utilized to screen options

• For over 600 itineraries, and fixed

technology/operational decisions, optimization

determines best mix of technologies

Numerous architecture, system, and

technology trades being conducted.

Key Findings to Date

• A sustainable exploration program must focus on

delivering value throughout its lifetime to all

stakeholders

• A Mars-back focus should be maintained

throughout the architecture and mission

development process

Schafer Highlights

Architecture Overview

• Emphasizes Gateway Architecture

• Architecture Fosters In Situ Resource Utilization(ISRU)

• L1 Refueling and resupply

• Direct return from lunar surface

• Off Earth Robotic Assembly, Set-up, and OperationFor All Infrastructure

• Robotic Reconnaissance Missions Select NearLunar Equator And South Pole Locations ForProbable Extended Presence And ContinuedExploration

• Assume One Crewed Mission Per Year Over 5-yearCampaign In Spiral-2

Drivers and Sensitivities

• CEV Mass Strongly Influences Propellant Required

• Radiation Shielding Of CEV Is Severe Penalty

• Launch Of Propellant Mass To LEO Dominates AllArchitectures

• CONUS Landing Stresses CEV For Direct Return

• LV Capabilities And Lift Mass To LEO

• CEV Crew Size

• Reliability Of Storage And Transfer Of CryoPropellant In Space

• ISRU Propellant Or LunOX Production EffectivenessFor Future Spiral-3 Missions

• Abort Scenarios For Crew Safety Determine SizeAnd Mass Of L1 Infrastructure

0

10

20

30

40

50

60

70

80

L1 8mt CEV L1 12mt CEV LEO 12mt CEV L1 12mt CEV,

8mt Lander

L1, 12mt CEV,

12mt Lander

LEO, 16mtCEV L1, 16mt CEV,

8mt Lander

L1, 16mt CEV

12mt Lander

Nu

mb

er o

f L

au

nch

es

Prop. CEV Lander Cargo Supplies

SpaceHab Highlights

Architecture Overview

• Maximize system modularity to the greatestextent possible

• Each element will have the capability tooperate alone or in conjunction with otherelements

• All non-crewed elements are launched oncommercial Expendable Launch Vehicles(ELVs) with a lift capability of at least 15metric tons.

• The Crew Exploration Vehicle (CEV) islaunched on a human rated launch system.

• The CEV is sized to accommodate fourcrewmembers.

• Reuse of systems

Key Technologies Identified to Date

• Automated Rendezvous, ProximityOperations and Docking (ARPOD)

• Liquid Cryo Propellant Management

• Extended-duration power generation(Nuclear Power)

• Interplanetary communications relay

• Regenerative ECLSS

• Radiation Shielding

AirLaunch LLC OptionAirLaunch LLC Option

Ground Launch OptionsGround Launch Options

SpaceXSpaceX

KistlerKistler

Launch ElementsLaunch ElementsLaunch ElementsLaunch ElementsS2S2S2S2S1S1S1S1

Future LSAM Derivative

S2CEV for crew

CCB for S1

Triple CCB for S2

S1Tanker for propellant

S1CXV for crew

t-Space Highlights

An Engine for Free Enterprise

• Pay-for-results rather than pay-for-analysis

• Businesses can grow from earnings

• NASA-commercial partnerships will build amore resilient system

• With NASA as an enabling partner, firms cantransform space into a net generator of taxrevenues instead of an endless consumer ofthem

An Open Frontier

• Government leadership rather thangovernment ownership

• Flotilla expeditions, not single vehicles

• Smaller, simpler vehicles

• For the first 20-40 expeditions, it will becheaper to use more propellant than tocreate new optimized vehicles (lunar lander)

• Simplicity equals reliability

• Enable commercial passenger markets

Mission Definition

• Land at south pole quickly

• Each expedition builds in-spaceinfrastructure

• Public must see understandable value

DESIGN

FY 04 FY 06 FY 08 FY 12 FY 14FY 10

STUDY

STUDY

CEV

CDR

RF

P

DESIGN

SRR PDR

PDR

Risk Reduction 2008 Demo

CEV Un-Crewed

Flight

DESIGN

Risk Reduction 2008 Demo

DESIGN

CEV Project

ESRT/HSRT EFFORTSTechnology

Infusion BAABAA

SYSTEM ENGINEERING AND INTEGRATIONS. Integrator RFP

ESRT/HSRT RESEARCHSafety Net

BAABAA

Spiral 1

Formulation

Approval

Spiral 1

Program

Approval

Spiral 1

Production

Approval

FABRICATE

Spiral 1

Design

ApprovalPHASE A:

MISSION DEFINITION

PHASE B:

PRELIMINARY DESIGN

PRE-PHASE A

ACTIVITIES

PHASE C:

FINAL DESIGN

PHASE D:

FABRICATE/OPERATE

B

C

A

D

AG

EN

CY

MIL

ES

TO

NE

S

RE

QU

IRE

ME

NT

S

DE

FIN

ITIO

N

SP

IRA

L I

PR

OJE

CT

S

RE

LA

TE

D

PR

OJE

CT

S

CEV Crewed

Flight

Non Traditional ApproachETO Potential Commercial Solution

DESIGN

FY 04 FY 06 FY 08 FY 12 FY 14FY 10

STUDY

STUDY

CEV

CDR

RF

P

DESIGN

SRR PDR

PDR

Risk Reduction 2008 Demo

CEV Un-Crewed

Flight

DESIGN

Risk Reduction 2008 Demo

DESIGN

CEV Project

ESRT/HSRT EFFORTSTechnology

Infusion BAABAA

SYSTEM ENGINEERING AND INTEGRATIONS. Integrator RFP

ESRT/HSRT RESEARCHSafety Net

BAABAA

Spiral 1

Formulation

Approval

Spiral 1

Program

Approval

Spiral 1

Production

Approval

FABRICATE

Spiral 1

Design

ApprovalPHASE A:

MISSION DEFINITION

PHASE B:

PRELIMINARY DESIGN

PRE-PHASE A

ACTIVITIES

PHASE C:

FINAL DESIGN

PHASE D:

FABRICATE/OPERATE

B

C

A

D

AG

EN

CY

MIL

ES

TO

NE

S

RE

QU

IRE

ME

NT

S

DE

FIN

ITIO

N

SP

IRA

L I

PR

OJE

CT

S

RE

LA

TE

D

PR

OJE

CT

S

CEV Crewed

Flight

DESIGN

FY 04 FY 06 FY 08 FY 12 FY 14FY 10

STUDY

STUDY

CEV

CDR

RF

P

DESIGN

SRR PDR

PDR

Risk Reduction 2008 Demo

CEV Un-Crewed

Flight

DESIGN

Risk Reduction 2008 Demo

DESIGN

CEV Project

ESRT/HSRT EFFORTSTechnology

Infusion BAABAA

SYSTEM ENGINEERING AND INTEGRATIONS. Integrator RFP

ESRT/HSRT RESEARCHSafety Net

BAABAA

Spiral 1

Formulation

Approval

Spiral 1

Program

Approval

Spiral 1

Production

Approval

FABRICATE

Spiral 1

Design

ApprovalPHASE A:

MISSION DEFINITION

PHASE B:

PRELIMINARY DESIGN

PRE-PHASE A

ACTIVITIES

PHASE C:

FINAL DESIGN

PHASE D:

FABRICATE/OPERATE

B

C

A

D

AG

EN

CY

MIL

ES

TO

NE

S

RE

QU

IRE

ME

NT

S

DE

FIN

ITIO

N

SP

IRA

L I

PR

OJE

CT

S

RE

LA

TE

D

PR

OJE

CT

S

CEV Crewed

Flight

Exploration Systems Mission Directorate

www.nasa.gov