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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