muirhead.brian

ARCHITECTING THE NEXT CREWED MISSIONS TO THE MOON

Brian MuirheadConstellation 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”

3

Integrated Architecture Analysis

Orion, Ares I and EVA Baseline

“Basis” Mission(may not meet reqts)

Surface System Design/Analysis

Altair Conceptand parametrics

Ares V Concepts

Lander Config, Unloading Strategy, P/L Mass, Volume

“Trade Set”Option &

Comparisons

Reserves & Margins

Methodology“Basis Mission” Buyback

Refine-ment

Cost, Risk, Scenario Analyses•Mobility•Outpost Buildup Rate•Resource Utilization•Commercial Involvement•International Partnerships

Element Concepts

System and Mission Recommendations

G&As from Lat 1 & 2

Cost, Risk Assessments

Integrated Performance

Continued Surface Scenario Assessments

TransporterTransporterGround Ops

44

Integrated Margins Analysis

),,,( ,, Lttjispt

VAres vmIPf Δ−

PM Reserve (Ares-V)

PgM Reserve

MGA (Altair + Orion + SA)

kg

Base Mass**

Req’d Del Capability†

TLI Stack Control Mass

Predicted Mass*

Calculated Gross Capability

PM Reserve (Altair + Orion + SA)

TLI Stack Control MassOrion 20,185 kgAltair 45,000 kgSA 900 kg

66,085

75,085

70,085

),( ,, LtjitTLI mMg

Total Margin(Altair + Orion + SA)

Expected Total Mass(Altair + Orion + SA)

Note: PM Reserve may be encumbered by threats and opportunities.Unencumbered PM Reserve = PM Reserve – E{T&O}

Most Likely GrossCapability (Ares-V)

♦ 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

Constellation’s Seven Projects

6

Ares- Launch Vehicle

Orion-Crew Exploration

VehicleExtravehicular

ActivitiesMission

Operations

Ground Operations Altair Lunar Surface Systems

77

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

Orion Development

Ares I Development

Commercial Crew/Cargo for ISS

Initial Orion Capability

1st Human Orion Flt.

Orion Production and Operations

Science Robotic Missions

Mars Expedition Design

Space Shuttle Ops

Lunar Lander Development

Ares V Development

Earth Departure Stage Development

Surface Systems DevelopmentEarly Design Activity

Lunar Outpost BuildupLunar Robotic Missions7th Human Lunar Landing

ISS Sustaining Operations SSP Transition…

Ares Project

8

Ares I – Crew Launch Vehicle

Serves as the long term crew launch capability for the U.S.

5 segment Shuttle-derived solid rocket booster

New liquid oxygen/liquid hydrogen upper stage using J-2X engine

First Stage

Upper Stage Engine

Orion CEV

Interstage

Instrument Unit

Encapsulated ServiceModule (ESM) Panels

Upper Stage Element

Orion Project

Orion – Crew Exploration Vehicle

Orion will support both International Space Station (ISS) and lunar missionsDesigned to operate for 180 days and up to 210 days docked to ISS or supporting outpost missions on the moon.Designed for lunar mission with 4 crew members Can accommodate up to 6 crew members to the ISSPotential to deliver pressurized and unpressurized cargo to the ISS

9

Launch Abort System

Crew Module

Service Module

Spacecraft Adapter

Ground Operations Project

Ares IVAB HB3

Ares INew ML

Ares ILC 39B

Ares ICrawler-Transporter

Ares VPad 39A Flame Deflector

Ares VPad 39A

Ares V Modified MLAres V

VAB HB1

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

Page 11

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

12

Lunar Crewed Mission Profile

MOONMOON

EARTHEARTH

LLO 100 km

Direct or Skip EntryERO

Up to 4 days LEO Loiter

EDS Performs TLI on FD5

Nominal Water Landing

Crew of 4 + 500 kg cargo

Altair performs LOI

100 kg return payload

Ares-1 Ascent Target

90 min. launch

separation

Orion 20.185 t at

TLI

Orion performs 3 Burn TEI up to 1,492 m/s

“Basis” Mission used to establish minimum content:

Sortie to Pole7 day stay4 crew members500 kg p/l down100 kg p/l upSingle Burn Lunar Orbit Insertion Burn at 891 m/s

Additional mission content evaluated during integrated architecture analysis

7405.13

Ares V 51 Series Trade Space Performance at Translunar Injection (Feb 08)

7330.13

CoreBooster

Standard CoreW/ 5 RS-68

Opt. Core Length / # Core Engines

5 SegmentPBAN

Steel CaseReusable

5 SegmentHTPB

Composite CaseExpendable

5.5 Segment PBAN

Steel CaseReusable

63.6t-2.5t

68.6t+2.5t

69.7t+3.6t

51.0.39 51.0.46

51.0.40

74.7t+8.6t

51.0.47

67.4t+1.3t

71.1t+5.0t

51.0.41 51.0.48

Engines: 6Spacers: 0



+5.0t

+6.1t

+6.1t

+3.7t

-2.3t

-3.6t

+5.0t

LCCR Study Reference LCCR Study Upgrade

Common Design Features

Composite Dry Structures for Core Stage, EDS & ShroudHeight = 116 m

Metallic Cryo Tanks for Core Stage & EDS

RS-68B Performance:Isp = 414.2 secThrust = 3547 k N @ vac

J-2X Performance:Isp = 448.0 secThrust = 1308 k N @ vac

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

Ares V Point of Departure Baseline

♦ Vehicle 51.0.48 • 6 Engine Core, 5.5 Segment PBAN Steel Case Booster• Provides Architecture Closure with Margin

♦ Maintaining Vehicle 51.0.47 with Composite HTPB Booster as future block change 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

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

Lunar Surface System Concept Elements

16

ATHLETELong-distance

Mobility System (2)

ATHLETELong-distance

Mobility System (2)

Small PressurizedRover (SPR)

Small PressurizedRover (SPR)

HabitationElement

HabitationElement

Common AirlockWith Lander

Common AirlockWith Lander

ISRU OxygenProduction Plant

ISRU OxygenProduction Plant

Power Support Unit (PSU)( Supports / scavenges from

crewed landers )

Power Support Unit (PSU)( Supports / scavenges from

crewed landers )PSU

(Facilitates SPR docking & charging)

PSU(Facilitates SPR

docking & charging)

HabitationElement

HabitationElement

LogisticsPantry

LogisticsPantry

Unpressurized RoverUnpressurized Rover

10 kW Array (net)10 kW Array (net)

2 kW Array (net)2 kW Array (net)

Conceptual Outpost Elements Conceptual Outpost Elements

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

18

Delta-V:3-Burn Lunar Orbit Insertion Sequence for Global Access

LOI-1

Capture maneuverLOI-3

LLO circularization

LOI-2

Plane change maneuver

•Trajectories are optimized based on lunar surface location and epoch to 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.

19

Low Lunar Orbit Loiter: Benefit to Global Access

No Extended loiter

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 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.

20

Ares-V Options*, Altair Mass* vs. Surface Access -->50% Temporal, 2nd TLI Opp, 1 Day Pre-TEI Loiter, +6 Days Post LOI Loiter

42500

43500

44500

45500

46500

47500

48500

49500

0 10 20 30 40 50 60 70 80 90 100

% Lunar Surface Access

Alta

ir M

ass

(kg)

51.0.47=74.7 t - 20.2 t (Orion) - 5 t (L3 PMR) = 49.5 t

51.0.48=71.1 t - 20.2 t (Orion) - 5 t (L3 PMR) = 45.9 t

+6 Days LOI

+6 Days LOI

+4 Days LOI+2 Days LOI

Crew Optimized, 891 m/s

Cargo Optimized, 891 m/s

1000 m/s

100% Temporal, 5th TLI Opp 90% Temporal, 2nd TLI Opp 50% Temporal, 2nd TLI Opp

+6 Days LOI

Crew Optimized, 950 m/s

Integrated Performance Assessment

* L3 Reserves applied to Ares-V and Altair,Altair Masses include 860 kg spacecraft adapter

Takeaway: Surface access is attainable through various trades oTakeaway: Surface access is attainable through various trades of Deltaf Delta--V, loiter, and temporal availability. V, loiter, and temporal availability.

System and Mission Recommendation

40000

45000

50000

0 10 20 30 40 50 60 70 80 90 100% Lunar Surface Access

Alta

ir M

ass

(kg)

50% Temporal6C C

6S S

†

A

B

CAres 51.0.48

Ares 51.0.47

Altair Reference: p804-D• Sized for 1000 m/s, propellants

loaded for 950 m/s• Sized for 5 days total LLO Loiter

Altair Reference: p804-D• Sized for 1000 m/s, propellants

loaded for 950 m/s• Sized for 5 days total LLO Loiter

Ares-V 51.0.47 - Option• 6-RS68B• 5 Segment Composite SRBs


Ares-V Reference: 51.0.48• 6-RS68B• 5.5 Segment Steel Reusable SRBs

Ares-V Reference: 51.0.48• 6-RS68B• 5.5 Segment Steel Reusable SRBs

D

Global access achieved with reduce temporal coverage (not anytime) and extended loiter (notional)


Extended LoiterD

♦ 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

22

Resulting Change in Ares V Point of Departure

CoreBooster

Standard CoreW/ 5 RS-68

Opt. Core Length / # Core Engines

5 SegmentPBAN

Steel CaseReusable

5 SegmentHTPB

Composite CaseExpendable

5.5 Segment PBAN

Steel CaseReusable

63.6t-2.5t

68.6t+2.5t

69.7t+3.6t

51.0.39 51.0.46

51.0.40

74.7t+8.6t

51.0.47

67.4t+1.3t

71.1t+5.0t

51.0.41 51.0.48




+5.0t

+6.1t

+6.1t

+3.7t-2.3t

-3.6t

+5.0t

Ref DDTERef Produc1 in 66

+$127M+$22M/yr1 in 62

+$898M+273M/yr1 in 63

+$600M+$30M/yr1 in 64

+$1.03B+$295M/yr1 in 59

+$727M+$52M/yr1 in 62

Lunar Transportation Figures of Merit

♦ Performance• Ability to support the lunar outpost• Mass to surface: crew & cargo• Robustness of margins by system• Surface coverage: global access

3CxAT_Lunar TIP 06 May 2008

Ares-V Options*, Altair Mass* vs. Surface Access -->50% Temporal, 2nd TLI Opp, 1day Pre-TEI Loiter, +4 Days Post LOI Loiter

42500

43500

44500

45500

46500

47500

48500

49500

0 10 20 30 40 50 60 70 80 90 100

% Lunar Surface Access

Alta

ir M

ass

(kg)

51.0.47=74.7 mT - 20.2 mT (Orion) - 5 mT (L3 PMR) = 49.5 mT

51.0.40=69.7mT - 20.2 mT (Orion) - 5 mT (L3 PMR) = 44.5 mT

51.0.48=71.1 mT - 20.2 mT (Orion) - 5 mT (L3 PMR) = 45.9 mT

Crew Optimized, 44185 kg, 891 m/s

Cargo Optimized, 46264 kg, 891 m/s

47139 kg, 1000 m/s

100% Temporal, 5th TLI Opp 90% Temporal, 2nd TLI Opp 50% Temporal, 2nd TLI Opp

Crew Optimized, 45765 kg, 950 m/s

51.0.46=68.6mT - 20.2 mT (Orion) - 5 mT (L3 PMR) = 43.4 mT add loiter add loiter

subtract 1 mT M

R

subtract 1 mT M

R

off load prop & subtract 1mT MR

Crew Optimized minus 1mT MR, sized for 1000 m/s, offload prop to 950 m/s, + 4 days LOI loiter, 44757 kg, resultant Cargo = 14.7 mT

Crew Optimized minus 1mT MR, sized for 950 m/s, + 4 days LOI loiter, 43485 kg, resultant Cargo = 13.0 mT

43002 kg, Cargo Capability 12.9 mT

Effects of Reducing Altair MR

* L3 Reserves applied to Ares-V and Altair,Altair Masses include 860 kg spacecraft adapter

♦ Affordability• DDT&E• Recurring• Budget wedge left for surface systems• Cost confidence

Page 56May 21st, 2008 SENSITIVE BUT UNCLASSIFIED (SBU)

LCCR-M (Trade Set 2) Cx Level Sandchart

$0

$2,000

$4,000

$6,000

$8,000

$10,000

$12,000

$14,000

FY08 FY10 FY12 FY14 FY16 FY18 FY20 FY22 FY24 FY26 FY28 FY30Fiscal Year

RY

$M

Lunar Surface SystemsProgram ReservesAltairEVAGround OperationsProgram IntegrationMission OpsAres VAres IOrionTotal NOA

♦ Risk• LOC / LOM• Technical performance risk• Schedule risk• Commonality

11

Trade Studies Attacked Risk Drivers of Minimal Functional Vehicle (aborts were “off the table”)

A

Task Option Risk Build‐Up by Subsystem

0.00E+00

5.00E‐02

1.00E‐01

1.50E‐01

2.00E‐01

2.50E‐01

3.00E‐01

Baseline 100 200 300 400 500 600 700 800 900 1000 1100 1200 1300 1400 1500 1274 :LDAC‐2

1273 :Design

Mass Increase [kg]

LOC

MMOD

Life Support

Thermal

Propulsion

Power

Avionics

Preliminary Results subject to revision during close‐outResults do not include placeholdersPreliminary Results subject to revision during close‐outResults do not include placeholders1 in 71 in 7

LDAC 2LDAC 2

Increasing Mass for LOC/LOM mitigationIncreasing Mass for LOC/LOM mitigation

♦ Operations / Extensibility• Facilities impacts• Operational flows• Mars feed-forward

18For NASA Internal Use Only

CO

NST

ELLA

TIO

N G

RO

UN

D O

PER

ATI

ON

S

Ground Systems DiscriminatorsROM Development Costs thru 2020

0

500,000

1,000,000

1,500,000

2,000,000

2,500,000

3,000,000

3,500,000

Baseline 45.0.2 51.00.40 51.00.46 51.00.47 51.00.48

VIE

SRPE

SPE

LPE

MLE

Operations

Stochastic Margins Analysis @TLI

♦ Stochastic analysis focused around trans-lunar injection (TLI)

),,,( ,, Lttjispt

VAres vmIPf Δ−

PM Reserve (Ares-V)

PgM Reserve

MGA (Altair + Orion + SA)

Base Mass**

Req’d Del Capability†

TLI Stack Control Mass

Predicted Mass*

Calculated Gross Capability

PM Reserve (Altair + Orion + SA)

TLI Stack Control MassOrion 20,185 kgAltair 45,000 kg*

*including 900 kg adapter

),( ,, LtjitTLI mMg

Total Margin(Altair + Orion + SA)

Expected Total Mass(Altair + Orion + SA)

Most Likely GrossCapability (Ares-V)

kg

PDF for Ares-V Delivery Capability (Various Designs)

0

0.01

0.02

0.03

0.04

0.05

0.06

0.07

0.08

0.09

60 62 64 66 68 70 72 74 76 78 80

mt

Pro

babi

lity/

mt

Ares 51.0.39

Ares 51.0.48

Ares 51.0.47

PDFs for Ares-V Delivery Capability

PDF with the 95th percentile at 74.7 mt, the 5th percentile at 69.7 mt, and some negative skewness. This was developed using engineering judgment.

PDF with the 95th percentile at 65.2 mt and the 5th

percentile at 62 mt, developed from a Monte Carlo analysis by SpaceWorks Engineering.

CDFs for Ares-V Delivery Capability

CDF for Ares-V Delivery Capability (Various Designs)

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

60 62 64 66 68 70 72 74 76 78 80

mt

Prob

abili

ty Ares 51.0.39Ares 51.0.48Ares 51.0.47

26

Ares 51.0.48 and Various Altair ΔV Capabilities

27

Ares 51.0.47 and Various Altair ΔV Capabilities

28

Probabilities of Having Adequate Margin: By Launch Vehicle and Cargo for Sortie and Outpost Missions

Critical Probability for Various LVs and Altair Loadings

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

0 500 1000 1500 2000 2500 3000 3500

DM Cargo/PMR (In Excess of 500 kg)

Pro

babi

lity

Ares 51.0.39 + Altair 804-D @ 891 m/s Ares 51.0.48 + Altair 804-D @ 891 m/sAres 51.0.47 + Altair 804-D @ 891 m/s Ares 51.0.48 + Altair 804-D @ 950 m/sAres 51.0.48 + Altair 804-D @ 1000 m/s

Stochastic margins assessment indicates

high probability of having adequate Program/Project

margins and reserve

Stochastic margins assessment indicates

high probability of having adequate Program/Project

margins and reserve

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

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

Page 31

This is a POD transportation architecture baseline not the final design

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

Back Ups

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

34

40000

45000

50000

0 10 20 30 40 50 60 70 80 90 100% Lunar Surface Access

Alta

ir M

ass

(kg)

System and Mission Recommendation

50% Temporal6C C

Ares-VAres-

VPlom

Degree of Ares

ISS/ Lunar

Common

Altair delta-v (m/s)

Additional Transportation

(Ares & G.O.) Cost (FY07 $M)*

Cargo Down

in Cargo Only Mode

(t)

Available Reserve @ TLI (t)% Surface Access @

50% TemporalSized

For Load DDT&E ($M)

Rec. ($M/yr) Prog Ares-V

Perform

Altair

Reserve Total Margin

6S S

* Additional cost as compared to the 51.0.39 PPBE budget submittal** P/L available with lander “kitted” for cargo mode and full prop loading

†

† Coverage based on coarse trajectory scans across the Metonic cycle. Additional surface coverage expected with further mission designrefinement.

A

A 51.0.47 1/59 Medium 1000 1000 +$1,556 +$303 14.6 2.3 5.0 6.5 50% 65%

B

B 51.0.48 1/62 High 950 950 +$1,044 +$55 13.8 0.1 5.0 6.3 50% 50%

C

C 51.0.48 1/62 High 1000 950 +$1,044 +$55 14.6** 1.6 5.0 4.2 40% 50%

Ares 51.0.48

Ares 51.0.47

Altair Recommendation:• Sized for 1000 m/s, propellants

Loaded for 950 m/s• Sized for 5 days total LLO

Loiter

Altair Recommendation:• Sized for 1000 m/s, propellants

Loaded for 950 m/s• Sized for 5 days total LLO

Loiter



Ares-V Recommendation: 51.0.48

• 6-RS68B• 5.5 Segment Steel Reusable

SRBs

Ares-V Recommendation: 51.0.48

• 6-RS68B• 5.5 Segment Steel Reusable

SRBs

D



Extended LoiterD

D 51.0.48 1/62 High 1000 950 +$1,044 +$55 14.7** 1.2 5.0 4.3 40% 70%

35

Crew: ~180 days back to Earth

13

10 ~500 days on Mars

Crew: Jettison droptank after trans-Mars injection~180 days out to Mars

8

Cargo:~350 days to Mars

2

Mars Mission Profile

4 Ares-V Cargo Launches1

CargoVehicles

4Aerocapture / Entry, Descent & Land Ascent Vehicle

3Aerocapture Habitat

Lander into Mars Orbit

5In-Situ propellant production for Ascent Vehicle

~26months

6 3 Ares-V Cargo Launches

CrewTransferVehicle

Ares-I Crew Launch7

9 Crew: Use Orion to transfer to Habitat Lander; then EDL on Mars

Crew: Ascent to high Mars orbit

11

Crew: Prepare for Trans-Earth Injection

12

~30months

Orion direct Earth return

14