1. ARCHITECTING THE NEXT CREWED
MISSIONS TO THE MOON
Brian Muirhead
Constellation Chief Architect
PM Challenge, 2009

2. Introduction/Takeaway
♦ Experience has shown us that integrated architecture
assessments are crucial for establishing stable configurations that
meet performance, cost and risk goals
♦ Isolated, “stovepiped” elements designs (i.e., Orion, Altair, Ares,
etc.) anchored only by “control masses” derived from a reference
mission are insufficient.
♦ Integrated architecture assessments allow for:
• Mission-level trades and optimization ensuring efficient vehicle designs
• Appropriate allocation of design margins
• Architecture-level functional allocations eliminating “I forgots”
2

3. Integrated Architecture Analysis
Cost, Risk System and Mission Recommendations
Assessments
Ares V Concepts
Integrated
Performance
Altair Concept
and parametrics
Ground Ops
Transporter Reserves & Refine-
“Basis” Mission Margins ment
(may not meet reqts)“Basis Mission” Buyback Methodology
Orion, Ares I
and EVA
Baseline Surface System Design/Analysis Cost, Risk, Scenario Analyses
•Mobility
Lander Config, •Outpost Buildup Rate
Unloading Strategy, •Resource Utilization
P/L Mass, Volume •Commercial Involvement
•International Partnerships Continued
Surface
Scenario
Assessments
“Trade Set”
G&As from Option &
Lat 1 & 2 Comparisons
Element Concepts
3

4. Integrated Margins Analysis
♦ Integrated margins assessments allow flexibility in allocation
♦ Avoids overdesign due to “margin on margins” – unique to exploration missions
♦ Stochastic approach allows architecture-level margin confidence levels
kg Note: PM Reserve may be encumbered by threats and opportunities.
Unencumbered PM Reserve = PM Reserve – E{T&O}
Calculated Gross Capability 75,085 f ( P t
Ares −V I sp , mi , j ,t , Δvt , L)
PM Reserve (Ares-V)
Most Likely Gross
Req’d Del Capability† 70,085 Capability (Ares-V)
PgM Reserve
TLI Stack Control Mass 66,085 t
g(MTLI mi, j,t ,L)
PM Reserve (Altair + Orion + SA)
Predicted Mass* Expected Total Mass
Total Margin (Altair + Orion + SA)
(Altair + Orion + SA)
MGA (Altair + Orion + SA)
Base Mass**
TLI Stack Control Mass
Orion 20,185 kg
Altair 45,000 kg
SA 900 kg
4
4

5. 5

6. Constellation’s Seven Projects
Orion-Crew
Ares- Launch Exploration Extravehicular Mission
Vehicle Vehicle Activities Operations
Ground Operations Altair Lunar Surface
Systems
6

7. NASA’s Exploration Roadmap
05 06 07 08 09 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25
Science Robotic Missions
Mars Expedition Design
7th Human
Lunar Robotic Missions Lunar Lunar Outpost Buildup
Landing
1st Human
Orion Flt.
Surface Systems Development
Early Design Activity Lunar Lander Development
Ares V Development
Earth Departure Stage Development
Orion Production and Operations
Orion Development
Initial Orion Capability
Ares I Development
Commercial Crew/Cargo for ISS
ISS Sustaining Operations
Space Shuttle Ops SSP Transition…
7
7

8. Ares Project
Ares I – Crew Launch Vehicle
Orion CEV
Encapsulated Service Serves as the long term crew
Module (ESM) Panels launch capability for the U.S.
Instrument Unit
Upper Stage 5 segment Shuttle-derived solid
Element rocket booster
Upper Stage
Engine Interstage New liquid oxygen/liquid
hydrogen upper stage using J-2X
engine
First Stage
8

9. Orion Project
Launch Abort System
Orion – Crew Exploration
Vehicle
Orion will support both
International Space
Station (ISS) and lunar missions
Designed to operate for 180 days
Crew Module and up to 210 days docked to
ISS or supporting outpost
Service Module missions on the moon.
Designed for lunar mission with
4 crew members
Spacecraft Adapter Can accommodate up to 6 crew
members to the ISS
Potential to deliver pressurized
and unpressurized cargo to the
ISS
9

10. Ground Operations Project
Ares I
Crawler-Transporter
Ares I
New ML
Ares I
Ares I
VAB HB3
LC 39B
Ares V
Ares V Pad 39A Flame Deflector
Modified ML
Ares V
VAB HB1
Ares V
Pad 39A
Page 10

11. Architecture Definition Introduction
♦ Constellation conducted a Lunar Capability Concept Review
(LCCR) in June 2008 to define an integrated Point of Departure
(POD)* for the transportation architecture including capabilities to:
• Deliver and return crew to the surface of the moon for short durations, i.e.
Human Lunar Return (HLR)
• Support a range of lunar exploration scenarios and possible surface system
architectures, including establishment of a lunar outpost
♦ Included in the LCCR were the Mission Concept Reviews for Ares
V and Altair (crewed and cargo) including
• Conceptual designs and key driving requirements
• Technology drivers and alternative designs
• Design concepts that meet mission and programmatic requirements
♦ Current capabilities of Ares I and Orion for the lunar missions
were assumed
♦ Lunar Surface System concepts were explored but no POD
selected
*This is a POD transportation architecture and NOT the final
baseline
Page 11

12. Lunar Crewed Mission Profile
MOON
“Basis” Mission used to establish minimum
content: Crew of 4 + 500 kg cargo
100 kg return payload
Sortie to Pole
7 day stay
4 crew members
500 kg p/l down
100 kg p/l up
Single Burn Lunar Orbit Insertion Burn LLO 100 km
at 891 m/s
Altair performs
Additional mission content evaluated during LOI Orion performs 3
integrated architecture analysis Burn TEI up to
1,492 m/s
Orion
20.185 t at
TLI
EDS Performs TLI
on FD5
Direct or Skip
Entry
ERO
Ares-1 Ascent Target
90 min.
launch Nominal Water
separation Landing
EARTH
Up to 4 days LEO Loiter 12

13. Ares V 51 Series Trade Space Performance at
Translunar Injection (Feb 08)
Common Design Features
Core Standard Core Opt. Core Length /
Booster W/ 5 RS-68 # Core Engines Composite Dry Structures
for Core Stage, EDS &
51.0.39
5 Segment +5.0t 51.0.46 Shroud
PBAN 63.6t 68.6t Height = 116 m
Steel Case -2.5t +2.5t
Reusable Engines: 6 Metallic Cryo Tanks for
Spacers: 1
+6.1t
+6.1t
Core Stage & EDS
5 Segment
51.0.40 +5.0t 51.0.47
RS-68B Performance:
HTPB 69.7t 74.7t
+8.6t Isp = 414.2 sec
Composite Case +3.6t
Expendable Engines: 6 Thrust = 3547 k N @ vac
Spacers: 1
-3.6t
-2.3t
J-2X Performance:
51.0.41 +3.7t 51.0.48
5.5 Segment Isp = 448.0 sec
PBAN 67.4t 71.1t
+1.3t +5.0t Thrust = 1308 k N @ vac
Steel Case
Reusable Engines: 6
Shroud Dimensions:
Spacers: 0
Barrel Dia. = 10 m
LCCR Study Reference LCCR Study Upgrade
Usable Dia. = 8.8 m
Barrel Length = 9.7 m
7405.13
7330.13

14. Ares V Point of Departure Baseline
♦ Vehicle 51.0.48
21.7 m
10 m
• 6 Engine Core, 5.5 Segment PBAN Steel Case Booster
• Provides Architecture Closure with Margin
23.2 m
♦ Maintaining Vehicle 51.0.47 with Composite HTPB
Booster as future block change option
• Final Decision on Ares V Booster at Constellation Lunar
10 m 116.2 m
SRR (2010)
• Additional Performance Capability if needed for Margin
or requirements
• Allows for competitive acquisition environment for
71.3 m booster
58.7 m
♦ Near Term Plan to Maintain Booster Options
• Fund key technology areas: composite cases, HTPB
propellant characterization
• Competitive Phase 1 Industry Studies
NOTE: These are MEAN numbers
Page 14

15. Altair Lunar Lander POD Baseline
♦ 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 hydrogen
propulsion
♦ Ascent stage:
• Hypergolic Propellants or Liquid
oxygen/methane
Page 15

16. Lunar Surface System Concept Elements
Conceptual Outpost Elements
10 kW Array (net)
10 kW Array (net)
2 kW Array (net)
2 kW Array (net)
Logistics
Logistics
Pantry
Pantry Habitation
Habitation
Power Support Unit (PSU)
Power Support Unit (PSU) Element Habitation
Element Habitation
(( Supports // scavenges from Element
Element Small Pressurized
Supports scavenges from Small Pressurized
crewed landers ))
crewed landers Rover (SPR)
Rover (SPR)
PSU
PSU
(Facilitates SPR
(Facilitates SPR
docking & charging)
docking & charging)
Common Airlock
Common Airlock
With Lander
With Lander
ATHLETE
ATHLETE ISRU Oxygen
ISRU Oxygen
Long-distance
Long-distance Production Plant
Production Plant
Mobility System (2)
Mobility System (2) Unpressurized Rover
Unpressurized Rover
16

17. Mission Design Drivers and Flexibility (example)
♦ Drivers:
• Surface Stay Time
• Anytime Return Capability
• Global Access
• Surface Mission Duration
• Spacecraft maximum mass
• Lunar payload delivery and return
♦ Mission design parameters traded to achieve global access:
• Delta-V:
− Orion fixed at 1492 m/s (including dispersions, 1417 m/s available for
translational maneuvers)
− Altair examined from 891m/s - 1350 m/s
− Earth Departure Stage fixed at 3175 m/s
• Low Lunar Orbit Loiter:
− Post-LOI 1 day nominal to +6 days extended
− Pre-TEI 1 day nominal to +5 days extended
• Temporal Availability (Availability over 18.6 year lunar nodal cycle)
− Assume 100% initial availability, trade availability for additional surface
locations
• Reserves/Margin Posture
17

18. Delta-V:
3-Burn Lunar Orbit Insertion Sequence for Global Access
LOI-2 •Trajectories are optimized based on
Plane change lunar surface location and epoch to
maneuver
minimize total propellant cost and
system wet mass.
•Forcing energy into the system by
increasing Delta-V rapidly increases
wet mass. Other mission design
techniques are used to gain global
access.
LOI-1
LOI-3
Capture maneuver
LLO circularization
18

19. Low Lunar Orbit Loiter:
Benefit to Global Access
No Extended loiter
•Map is a Mercator projection
of entire lunar surface.
•White regions represent
difficult to reach locations
due to earth-moon geometry.
•When Delta-V is constrained
due to mass limits, loiter in
Extended loiter lunar orbit prior to descent is
a powerful knob for
additional access.
•Additional loiter means
increased total in-space
mission duration, while
maintaining fixed surface
stay.
19

20. Integrated Performance Assessment
Ares-V Options*, Altair Mass* vs. Surface Access -
->50% Temporal, 2nd TLI Opp, 1 Day Pre-TEI Loiter, +6 Days Post LOI Loiter
100% Temporal, 5th TLI Opp 90% Temporal, 2nd TLI Opp 50% Temporal, 2nd TLI Opp
49500 51.0.47=74.7 t - 20.2 t (Orion) - 5 t (L3 PMR) = 49.5 t
48500
+6 Days LOI
1000 m/s
47500
Altair Mass (kg)
+6 Days LOI
46500 +6 Days LOI
+4 Days LOI
+2 Days LOI
51.0.48=71.1 t - 20.2 t (Orion) - 5 t (L3 PMR) = 45.9 t
Cargo Optimized, Crew Optimized,
45500
891 m/s 950 m/s
44500
Crew Optimized,
43500 891 m/s
42500
0 10 20 30 40 50 60 70 80 90 100
* L3 Reserves applied to Ares-V and Altair, % Lunar Surface Access
Altair Masses include 860 kg spacecraft adapter
Takeaway: Surface access is attainable through various trades of Delta-V, loiter, and temporal availability.
of Delta-
20

21. System and Mission Recommendation
50000
C 6 C l
ora
Ares 51.0.47 51.0.47 - Option
Ares-V 51.0.47 - Option mp Global access achieved
Ares-V %
Te Global access achieved
with reduce temporal
• • 6-RS68B
6-RS68B 50 with reduce temporal
• • 55Segment Composite SRBs coverage (not anytime)
coverage (not anytime)
Segment Composite SRBs and extended loiter
A and extended loiter
(notional)
(notional)
Altair Mass (kg)
S 6 S B
45000 Extended Loiter D
Ares 51.0.48 D
Ares-V Reference: 51.0.48
Ares-V Reference: 51.0.48 C
•• 6-RS68B
6-RS68B
•• 5.5 Segment Steel Reusable SRBs
5.5 Segment Steel Reusable SRBs
Altair Reference: p804-D
Altair Reference: p804-D
• • Sized for 1000 m/s, propellants
Sized for 1000 m/s, propellants
loaded for 950 m/s
loaded for 950 m/s
• • Sized for 55days total LLO Loiter
Sized for days total LLO Loiter
40000
0 10 20 30 40 50 60 70 80 90 100
†
% Lunar Surface Access
♦ Point D is the nominal baseline design point which includes 950 m/s
load and 5 day low lunar orbit loiter
♦ Points B & C are with Altair 950 m/s load without loiter
♦ Point A would be enabled by Ares 51.0.47 and allow Altair to load to
1000 m/s
♦ Full global access can be achieved with combination of mission timing,
duration and/or additional loiter Page 21

22. Resulting Change in Ares V Point of
Departure
Core Standard Core Opt. Core Length /
Booster W/ 5 RS-68 # Core Engines
51.0.39
5 Segment +5.0t 51.0.46
63.6t Ref DDTE 68.6t +$127M
PBAN
-2.5t Ref Produc +2.5t +$22M/yr
Steel Case 1 in 66 1 in 62
Engines: 6
Reusable Spacers: 1
+6.1t
+6.1t
5 Segment
51.0.40 +5.0t 51.0.47
HTPB 74.7t +$1.03B
69.7t +$898M
+8.6t +$295M/yr
Composite Case +3.6t +273M/yr
1 in 63 Engines: 6 1 in 59
Expendable Spacers: 1
-3.6t
-2.3t
51.0.41 +3.7t 51.0.48
5.5 Segment
PBAN 67.4t +$600M 71.1t +$727M
+1.3t +$30M/yr +5.0t +$52M/yr
Steel Case
1 in 64 Engines: 6 1 in 62
Reusable Spacers: 0
22

23. Lunar Transportation Figures of Merit
♦ Performance ♦ Affordability
• Ability to support the lunar outpost • DDT&E
• Mass to surface: crew & cargo • Recurring
• Robustness of margins by system • Budget wedge left for surface systems
• Surface coverage: global access • Cost confidence
Effects of Reducing Altair MR
LCCR-M (Trade Set 2) Cx Level Sandchart
Ares-V Options*, Altair Mass* vs. Surface Access -
->50% Temporal, 2nd TLI Opp, 1day Pre-TEI Loiter, +4 Days Post LOI Loiter
Lunar Surface Systems
100% Temporal, 5th TLI Opp 90% Temporal, 2nd TLI Opp 50% Temporal, 2nd TLI Opp $14,000 Program Reserves
49500 Altair
51.0.47=74.7 m T - 20.2 mT (Orion) - 5 mT (L3 PMR) = 49.5 mT EVA
Ground Operations
Program Integration
48500 $12,000 Mission Ops
Ares V
Ares I
47500 47139 kg, 1000 m/s Orion
$10,000 Total NOA
Altair Mass (kg)
46500
off load prop & subtract 1mT MR
RY $M
$8,000
51.0.48=71.1 m T - 20.2 mT (Orion) - 5 mT (L3 PMR) = 45.9 mT
45500
subtract 1 mT MR
Cargo Optimized,
Crew Optimized minus 1mT MR, sized for 1000 m/s, offload prop to
subtract 1 mT MR
46264 kg, 891 m/s
950 m/s, + 4 days LOI loiter, 44757 kg, resultant Cargo = 14.7 mT
Crew Optimized, $6,000
45765 kg, 950 m/s
44500
51.0.40=69.7mT - 20.2 m T (Orion) - 5 m T (L3 PMR) = 44.5 m T
Crew Optimized minus 1mT MR, sized f or 950 m/s, + 4
Crew Optimized, days LOI loiter, 43485 kg, resultant Cargo = 13.0 mT
43500 44185 kg, 891 m/s $4,000
add loiter add loiter
51.0.46=68.6m T - 20.2 mT (Orion) - 5 m T (L3 PMR) = 43.4 mT
43002 kg, Cargo Capability 12.9 mT
42500 $2,000
0 10 20 30 40 50 60 70 80 90 100
* L3 Reserves applied to Ares-V and Altair, % Lunar Surface Access
Altair Masses include 860 kg spacecraft adapter
$0
FY08 FY10 FY12 FY14 FY16 FY18 FY20 FY22 FY24 FY26 FY28 FY30
Fiscal Year
CxAT_Lunar TIP 06 May 2008 3
May 21st, 2008 SENSITIVE BUT UNCLASSIFIED (SBU) Page 56
♦ Risk ♦ Operations / Extensibility
• LOC / LOM • Facilities impacts
• Technical performance risk • Operational flows
• Schedule risk • Mars feed-forward
• Commonality
Ground Systems Discriminators
Trade Studies Attacked Risk Drivers of Minimal Functional Vehicle (aborts were “off the table”)
ROM Development Costs thru 2020
3,500,000
Preliminary Results subject to revision during close‐out
1 in 7 Results do not include placeholders 3,000,000
CONSTELLATION GROUND OPERATIONS
VIE
Task Option Risk Build‐Up
by Subsystem
3.00E‐01
2,500,000
SRPE
A
2.50E‐01
2,000,000
SPE
1,500,000
2.00E‐01 LPE
MMOD
Life Support
1,000,000
1.50E‐01
Thermal
MLE
LOC
Propulsion
Power
Avionics
500,000
1.00E‐01
Operations
LDAC 2 0
Baseline 45.0.2 51.00.40 51.00.46 51.00.47 51.00.48
5.00E‐02
Increasing Mass for LOC/LOM mitigation
0.00E+00
Baseline 100 200 300 400 500 600 700 800 900 1000 1100 1200 1300 1400 1500 1274 : 1273 :
LDAC‐2 Design
Mass Increase [kg]
18
For NASA Internal Use Only
11
Page 23

24. Stochastic Margins Analysis @TLI
kg
Calculated Gross Capability f ( PAres −V I sp , mi , j ,t , Δvt , L)
t
PM Reserve (Ares-V)
Most Likely Gross
Req’d Del Capability† Capability (Ares-V)
PgM Reserve
TLI Stack Control Mass
t
PM Reserve (Altair + Orion + SA)
g (M TLI mi , j ,t ,L)
Predicted Mass* Expected Total Mass
Total Margin (Altair + Orion + SA)
(Altair + Orion + SA)
MGA (Altair + Orion + SA)
Base Mass** TLI Stack Control Mass
Orion 20,185 kg
Altair 45,000 kg*
*including 900 kg adapter
♦ Stochastic analysis focused around trans-lunar injection (TLI)
Page 24

25. PDFs for Ares-V Delivery Capability
PDF for Ares-V Delivery Capability (Various Designs)
0.09
0.08
0.07
0.06
Probability/mt
0.05 Ares 51.0.39
Ares 51.0.48
0.04 Ares 51.0.47
0.03
0.02
0.01
0
60 62 64 66 68 70 72 74 76 78 80
mt
PDF with the 95th percentile at 65.2 mt and the 5th PDF with the 95th percentile at 74.7 mt, the 5th percentile at
percentile at 62 mt, developed from a Monte Carlo 69.7 mt, and some negative skewness. This was developed
analysis by SpaceWorks Engineering. using engineering judgment.
Page 25

26. CDFs for Ares-V Delivery Capability
CDF for Ares-V Delivery Capability (Various Designs)
1
0.9
0.8
0.7
0.6
Probability
Ares 51.0.39
0.5 Ares 51.0.48
Ares 51.0.47
0.4
0.3
0.2
0.1
0
60 62 64 66 68 70 72 74 76 78 80
mt
Page 26

27. Ares 51.0.48 and Various Altair ΔV Capabilities
27

28. Ares 51.0.47 and Various Altair ΔV Capabilities
28

29. Probabilities of Having Adequate Margin: By Launch
Vehicle and Cargo for Sortie and Outpost Missions
Critical Probability for Various LVs and Altair Loadings
1
0.9
0.8
0.7 Stochastic margins
Stochastic margins
assessment indicates
assessment indicates
0.6 high probability of having
high probability of having
Probability
adequate Program/Project
adequate Program/Project
0.5 margins and reserve
margins and reserve
0.4
0.3
0.2
0.1
0
0 500 1000 1500 2000 2500 3000 3500
DM Cargo/PMR (In Excess of 500 kg)
Ares 51.0.39 + Altair 804-D @ 891 m/s Ares 51.0.48 + Altair 804-D @ 891 m/s
Ares 51.0.47 + Altair 804-D @ 891 m/s Ares 51.0.48 + Altair 804-D @ 950 m/s
Ares 51.0.48 + Altair 804-D @ 1000 m/s
Page 29

30. Lunar Transportation Architecture Summary
♦ Ares-V
• Ares-V 51.0.48, maximizes commonality between
Lunar and Initial Capabilities:
− 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 of Ares-V 51.0.47
♦ Altair
• 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 and system flexibility
− Size Altair tanks for 1,000 m/s LOI delta-v
− Size for an additional 4 days of Low-Lunar Orbit loiter
♦ 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
• Maintain emphasis on evolution of Orion Block 2 to
support lunar Outpost missions

31. Lunar Architecture Technical Summary
♦ The Constellation Program has completed extensive design, cost and
risk analysis studies of lunar transportation options and developed an
adequately closed Point of Departure (POD) transportation architecture
for the CxP Lunar Capability including capabilities to:
• Deliver and return crew to the surface of the moon for short durations,
Human Lunar Return (HLR) capability
• Enable establishment of a lunar outpost architecture
• Support a range of mission campaigns and possible lunar surface
architecture options
♦ Ares, Altair, Orion, EVA and GOP have completed extensive design,
performance, cost and risk analysis to establish this baseline
♦ Lunar Surface Systems (LSS) has provided a feasible set of surface
system configurations, vehicles and operational concepts to support
the validation of the transportation system
This is a POD transportation architecture baseline
not the final design
Page 31

32. Introduction/Takeaway
♦ Experience has shown us that integrated architecture
assessments are crucial for establishing stable configurations
that meet performance, cost and risk goals
♦ Isolated, “stovepiped” elements designs (i.e., Orion, Altair, Ares,
etc.) anchored only by “control masses” derived from a
reference mission are insufficient.
♦ Integrated architecture assessments allow for:
• Mission-level trades and optimization ensuring efficient vehicle designs
• Appropriate allocation of vehicle design margins
• Architecture-level functional allocations eliminating “I forgots”
♦ Details on the performance of the architecture elements and
how they operate together is critical to maintaining a viable
architecture
32

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

34. System and Mission Recommendation
50000
6 l
C C po
ra
Ares 51.0.47 51.0.47--Option
Ares-V 51.0.47 Option
Ares-V m
• • 6-RS68B Te
6-RS68B %
• • 55Segment Composite SRBs 50 Global access achieved
Segment Composite SRBs Global access achieved
with reduce temporal
with reduce temporal
A coverage (not anytime)
coverage (not anytime)
and extended loiter
and extended loiter
(notional)
Altair Mass (kg)
(notional)
S 6 S B
Extended Loiter D
45000 Ares-V Recommendation:
Ares 51.0.48 D
Ares-V Recommendation:
51.0.48 C
51.0.48
• • 6-RS68B
6-RS68B
• • 5.5 Segment Steel Reusable
5.5 Segment Steel Reusable Altair Recommendation:
Altair Recommendation:
SRBs
SRBs • • Sized for 1000 m/s, propellants
Sized for 1000 m/s, propellants
Loaded for 950 m/s
Loaded for 950 m/s
• • Sized for 55days total LLO
Sized for days total LLO
Loiter
Loiter
40000
0 10 20 30 40 50 60 70 80 90 100
†
% Lunar Surface Access
Additional
Altair delta-v Transportation Cargo
Degree Down Available Reserve @ TLI (t)
(m/s) (Ares & G.O.) Cost % Surface
Ares- of Ares (FY07 $M)* in
V Access @
Ares-V ISS/ Cargo
50%
Plom Lunar Only Altair
Sized DDT&E Rec. Ares-V Temporal
Common Load Mode Prog
For ($M) ($M/yr) (t) Perform Total
Reserve
Margin
A 51.0.47 1/59 Medium 1000 1000 +$1,556 +$303 14.6 2.3 5.0 6.5 50% 65%
B 51.0.48 1/62 High 950 950 +$1,044 +$55 13.8 0.1 5.0 6.3 50% 50%
C 51.0.48 1/62 High 1000 950 +$1,044 +$55 14.6** 1.6 5.0 4.2 40% 50%
D 51.0.48 1/62 High 1000 950 +$1,044 +$55 14.7** 1.2 5.0 4.3 40% 70%
* Additional cost as compared to the 51.0.39 PPBE budget submittal † Coverage based on coarse trajectory scans across the Metonic cycle.
** P/L available with lander “kitted” for cargo mode and full prop loading Additional surface coverage expected with further mission design
refinement. 34

35. Mars Mission Profile
10 ~500 days on Mars
In-Situ propellant production for Ascent 5
11 Crew: Ascent to high Mars
Vehicle
Aerocapture / Entry, Descent & Land Ascent orbit
4
Vehicle 12 Crew: Prepare for Trans-
Earth Injection
Aerocapture Habitat
Lander into Mars Orbit 3
9 Crew: Use Orion to
transfer to Habitat Lander;
Cargo: then EDL on Mars
2 ~350 days
to Mars
8 Crew: Jettison drop
tank after trans-Mars injection
~180 days out to Mars
13 Crew: ~180 days
Cargo back to Earth
Crew
Vehicles
Transfer
Vehicle
7 Ares-I Crew Launch
4 Ares-V Cargo
6 3 Ares-V Cargo Launches
1 Launches
~26 ~30
months months
14 Orion direct
Earth return
35