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Joint Propulsion Conference

Dr. George Sowers Space Systems Company

July 2005

July_05 1 Reliable & Versatile Family

ed ed ed ed ed ed tir tir tir tir tir tir Re Re Re Re Re Re

Atlas I II Atlas IIA Atlas IIAS Atlas IIIA Atlas IIIB -400 Atlas V -500 AC -69 AC -102 AC -105 AC -108 AC -201 AC -204 AV -001 AV -003 Jul 1990 Dec 1991 Jun 1992 Dec 1993 May 2000 Feb 2002 Aug 2002 Jul 2003

8/11 10/10 23/23 30/30 2/2 4/4 3/3 2/2

Legend: First Flight X/Y X successes in Y total flights • 76 Consecutive Successful Atlas Flights • 8 of 8 First Flight Successes • 100% Mission Success Atlas II, IIA, IIAS, III & V Families • 485 Total Launch Successes Since Atlas Program Inception Mission Success —One Launch at a Time

July_05 2 Atlas Evolution History

Atlas I/II Family Atlas III Family Atlas V Family

5m PLF 30 GSO Kit

26 Single Avionics Engine Common Upgrade 22 Centaur Centaur

3.8m 18 Common LO2 Core Tank Booster Stretch 14

10 Liquid SRBs Strapons 6 RD -180 SRBs Engine Atlas I Atlas IIAS Atlas IIIA Atlas IIIB Atlas V Atlas V Atlas V 407 km (220 nm) Circ. Capability (mT) Capability Circ. nm) (220 km 407 2 Atlas II (SEC) (DEC) (400 Series) (500 Series) (HLV) Atlas IIA (0 -3 SRBs) (0 -5 SRBs) First Flight 7/90 12/93 5/00 2/02 8/02 7/03 2008

Demonstrated Low Risk Evolutionary Development

July_05 3 Key Launch System Considerations • Safety & performance vs affordability – Can we have all three? • Near term progress vs optimal system – Can near term progress lead to optimal system down the road? • National systems vs NASA system – Can NASA & DoD synergize infrastructure?

July_05 4 Future EELV Launch Market

Requires Atlas/EELV derived vehicles

25

20 Cargo LV (Moon, Mars) CEV Launch Vehicle 15 ISS Cargo Resupply

10 NASA Science

Number Number ofMissions DoD HLV 5 DoD

0

2004 2005 2006 2007 2008 2009 2010 2011 2012 2013 2014 2015 2016 2017 2018 2019 2020 Launch Year Can be met with existing Atlas/EELV

NASA/DoD Synergy Doubles Flight Rate

July_05 5 Atlas V Operational Capability 30 30/yr VAFB 24 6/yr Month Surge Cape with 2 MLPs & Exploration VAFB 20 6/yr 2 VIFs 19/yr 24/yr Tooling Limit VAFB ISS Cargo Cape 12 -month 6/yr with Surge 2 MLPs

17/yr IV Cape 10 VAFB Annual Launch Rate Launch Annual Delta IV 12/yr Cape 12/yr

Atlas V Current VAFB

Atlas V Cape Projected Atlas V Current Atlas V Cape with Cape with USG Production Launch Ops Additional Additional Requirements Capacity Capacity MLP MLP & VIF Atlas V Capabilities Exceed USG Manifest Requirements

July_05 6 Atlas Evolution Philosophy

• Evolutionary Approach Minimizes Cost, Risk & Schedule

• Every Phase Maintains Common Fleet Serving All Customers

• Launch Fleet Family Designed Around Common Elements

• Reliability Enhancements and Launch Vehicle Health Monitoring (LVHM) Benefit All Customers

Sustainable,Sustainable, AffordableAffordable andand CredibleCredible

July_05 7 Atlas Evolution

Atlas V Family Phase 1 Family Phase 2 Family Phase 3 Addition Baseline Phase 1 Phase 2 Phase 3A Phase 3B HLV (Wide Body Centaur) (Wide Body Booster) (5 Body) (5 Body) (9 -28 mT LEO) (9 -40 mT LEO) (9 -74 mT LEO) (107 mT) (54 -140 mT) (33 mT w/ Options) (45 mT w/ Options) (90 mT w/ Options) -or -

7.2M PLF 8.4M PLF

5.4M Cent. Tank

1 to 4 RL10’s

5.4M Booster Tank Cluster 5.4M CCB 8.4M Tank 5 RD -180’s 1 to 2 RD -180’s

Existing Pad and Existing Pad and Existing Pad and New Launch New Launch Infrastructure Infrastructure Infrastructure Site Site Centaur Engine Out Centaur and Booster Engine Out Atlas Evolution Meets Space Exploration Needs

July_05 8 Integrated Cryogenic Evolved Stage (ICES) Development Risk Summary

Hardware Element Prior Flight Experience Comments Phase 1 5m PLF Atlas V and Flight proven Avionics Atlas V Relocated

Software Atlas V Updated to accommodate multiple engines and engine out Tank Structure Centaur moncoque design. Aluminum friction stirwelded tank. IRAD Shuttle ET Al. friction stirweld demonstration (2003/4). BAA 2005 Dry Structure Atlas and Shuttle ET Combination of aluminum and composite Insulation Commercial industry Vacuum insulation panels for common IB Pneumatics* Centaur Existing bottles and valves, new plumbing Reaction Control System* Centaur Existing bottles and thrusters, new plumbing Propulsion RL10 Requalified for new inlet conditions Vertical Integration Facility LC-41 Minor modifications to platforms. Mobile Launch Platform LC-41 Minor umbilical height changes Launch Site LC-41 Increase LH2/LO2 supply Booster Atlas V Unchanged existing booster. *Integrated propulsion, required for flexible in -space use, requires new development

Repackaged existing hardware Requalified /minor changes to New Hardware Existing hardware

Common Element Approach Minimizes ICES Risk

July_05 9 LM has Extensive Recent Cryo Experience

• Centaur’s history includes – 1, 2 or 3 burn missions (7 burns conducted as demo) – Settled and zero -G coasts – 5 recent Centaur development programs

768,370

250 209 800,000 700,000 TOTAL CRYO TOTAL CRYO 200 600,000 UPPER STAGE UPPER STAGE 150 114 500,000 ENGINE OPERATING 400,000 165,254 STARTS (since 100 40 TIME (sec) 300,000 ~1990) 200,000 50 10 (since ~1990) 60,480 100,000 0 0 Ariane Delta Centaur HII Ariane Delta47,602Centaur HII

LM’s Broad In -Space Experience Benefits Future Cryogenic Stages

July_05 10 Evolved Upper Stage Extensibility • Common Cryogenic Stage Supporting All Exploration Transportation Functions In -Space DoD Space Operations (EDS, LOI, TEI) Lunar Lander Vehicle (LSAM)

Common In -Space Upper Stage Propellant Depot ICES

Integrated Cryogenic Deep -Space Mars Return Evolved Stage Injection Stage

tank

Mars LH 2 tank LO 2 Propellant Depot Earth Return (TEI) tank

Evolved Upper Stage Supports Multiple In -space Applications

July_05 11 ICES Common Element Design

Common Forward Adapter

Common Domes, Insulation, Intermediate Multiple Length Bulkhead Barrel Sections

Kitable Avionics, Propulsion (Short Duration, Long Duration) Common Aft Thrust Structure Common Engine RL10A -4-2 1, 2, 4 or 6 Modular Design Maximizes Utility, Minimizes Risk & Cost

July_05 12 Phase 2 Booster Development Risk Summary

Hardware Element Prior Flight Experience Comments Avionics Atlas V Dual existing BRCU's accomodates dual RD180's Software Atlas V Updated to accommodate multiple engines and engine out Tank Structure Atlas V & Shuttle ET design Aluminum friction stirwelded isogrid tank. heritage Similar in construction to Shuttle ET. Dry Structure Atlas and Shuttle ET Combination of aluminum and composite Pneumatics Atlas V Existing bottles and valves, new plumbing Propulsion RD180 Unchanged RD180 - Same structure & plumbing interfaces Vertical Integration Facility LC-41 Existing VIF building & infrastructure. Platform modifications Mobile Launch Platform LC-41 Same external footprint/interfaces as existing MLP, Larger opening, taller structure

Launch Site LC-41 Existing infrasturcture and auto-couplers. Increased LH2/LO2 supply

Repackaged existing hardware Requalified /minor changes to New Hardware Existing hardware

Common Element Approach Minimizes Development Risk

July_05 13 Atlas/EELV Common Fleet (Phase 2 Family)

80

70 CLV 60 6x Centaur 50 6 Number of 5 40 Solids 4 3 2 30 1 0 2 20 1 0 407 km (220 nm) Circ. Capability (mT) Capability Circ. nm) (220 km 407 10 Phase 1 Family (Ref.)

Single RD -180 Dual RD -180

Current DoD/NASA Market Potential DoD Growth Potential NASA Growth

SDV Medium SDV Sidemount & In -line Heavy Common Fleet with Existing Infrastructure Meets All USG Requirem ents

July_05 14 Crew Launch Vehicle (CLV)

CEV with Abort System

5.4m Centaur, 1.5x Current Volume Fault -Tolerant Avionics with Fault -Tolerant LVHM System (Kit) Phase 1 Back -up Flight Control System (Kit) Phase 2 (if required) 4 RL -10 Engines Atlas V Booster 5.4 -m Booster, 1.7x Current Volume 1 RD -180 Engine 2 RD -180 Engines

PhasePhase 1 1 PhasePhase 2 2 ••12.412.4 mT mT Capability Capability 220 220 nm nm Circ. Circ. ••22.522.5 mT mT Capability Capability 220 220 nm nm Circ. Circ. ••13.313.3 mT mT Capability Capability (6 (6 RL RL -10s-10s & & 1.5x 1.5x Centaur) Centaur) ••28.028.0 mT mT (6 (6 RL RL -10s-10s & & 3.5x 3.5x Centaur) Centaur) ••TrajectoriesTrajectories Tailored Tailored to to Eliminate Eliminate Black Black Zones Zones ••TrajectoriesTrajectories Tailored Tailored to to Eliminate Eliminate Black Black Zones Zones Atlas CLV Investment Enables Cargo LV with Minimal Additional Investment

July_05 15 System -Level Human Rating

Reliability Health Monitoring • Fault -Tolerant Systems • Monitor Critical Systems • Centaur and Booster Engine - Using Independent Fault Out Capability Tolerant Failure Sensing System • Demonstrated Reliability L • Situational Awareness through high launch rate V H • Vehicle Characterization e • Fly Monitoring System on All y a t i lt Missions • Rigorous, closed -loop il h b M a • Engine Out Detection and processes li o e Human n Abort Commands R it • Experienced People Rated o V r Intact CEV Abort Capability L in E Spaceflight g System • Catastrophic LV failures minimized Intact CEV Abort Capability • Abort to under most engine failures System Level Approach Meets Space Exploration Needs

July_05 16 Atlas Reliability Improvement

Atlas II Demonstrated 18 Atlas V Design Reduced POF (63 of 63) Atlas V Design Reduced POF byby Factor Factor of of 2.65 2.65 16 •Engines,•Engines, Staging Staging Events, Events, PartsParts Eliminated Eliminated •Increased•Increased Redundancy Redundancy Phase 2 Design Incorporates 14 •AIII/V Demonstrated 10 of 10 Phase 2 Design Incorporates •AIII/V Demonstrated 10 of 10 EngineEngine Out Out for for Booster Booster and and CentaurCentaur 12 •Reduce•Reduce POF POF by by a a Factor Factor of of 1.87 1.87 65% confidence

10 Atlas V Phase 1 Phase 2

8 50% Confidence 74% confidence 92% confidence

6 Mission Reliability Requirement (0.99325) 4 Failures per 1000Flights per Failures R=0.997 @ 65% 2 9 mT 13 mT R=0.998 @ 50% 21.5 mT 0 DemonstratedDemonstrated SuccessSuccess ++ ProgramProgram ContinuityContinuity

July_05 17 Crew LV (CLV) and Cargo LV ( CaLV ) Development Plan, Phase 2

CY ’05 ’06 ’07 ’08 ’09 ’10 ’11 ’12 ’13 ’14 ’15 ’16 CEV First Moon Demo ISS Crew Servicing Mission CEV Flights Flights Crewed CEV NR Integration Flight CEV Demo SRR/ Flights CEV SDR PDR CDR VR 1 2 3 crew 70 mT Architecture

Upper Stage Development Moon Mission SRR/ First unit 3 launches CaLV 71 day span SDR PDR CDR VR (37 w/option) demo Booster Development First unit Pathfinder Site Mods VIF 1 mods, MLP mods, GSE Crew access/egress

~160 mT SRR/ SDR PDR CDR VR 7-m PLF Development Credibly Supports First unit NASA Early ILC Pathfinder NASA Early ILC CaLV Site Mods New MLP (VIF 2, MLP 2 Option)

July_05 18 Atlas/EELV Development Comparisons

AtlasAtlas III/V III/V NRE NRE Actuals Actuals AtlasAtlas Phase Phase 2 2 LV LV NRE NRE ROM ROM ••$YB$YB Total* Total* ••$(1.05Y)B$(1.05Y)B Total, Total, In In -space-space synergy synergy not not included included ••RDRD -180-180 Engine Engine Dev Dev ••OptionalOptional Launch Launch Site Site Infrastructure Infrastructure ••LaunchLaunch Vehicle Vehicle ••CLVCLV = = single single body body w/6RL10: w/6RL10: 28.028.0 mT mT ••LCLC -41-41 Launch Launch Site Site ••CaLVCaLV == three three body body w/6RL10: w/6RL10: 74.474.4 mT mT 1000 First un -Crewed CLV Flight First Crewed CLV Flight 800

Human System 600 Site + large PLF + CLV 3 body 400 Phase 2 ILC Optional VIF 2, MLP 2

200 Phase 1 First Moon Atlas III/V Mission Development* Constant Year 2005 $M 0 CaLV ILC 1995 1996 1997 1998 1999 2000 2001 2002 2003 2004 2005 2006 2007 2008 2009 2010 2011 2012 2013 2014 2015 2016 2017 2018 2019

*Does Not Include SLC3E Upgrade or RD -180 CoProduction Atlas III/V History Demonstrates Development Credibility

July_05 19 USG Spacelift Options (70mT Architecture) Today Future 1 USG Cost Market = DOD Market = DOD + ($CY05) + ISS ISS + Exploration $XB* USG at a Crossroads 2 y rg e $X+12B** n y S D O //D 3 A S A t $X+3B** EELV N lee d F xe Mi 4 NASA/DOD Independent Systems

STS Orbiter Retirement $X+10B**

*Note: Does not include NASA/DoD synergy, in -space synergy or rate benefits **Note: SDV Cost Reference. NASA -Industry ISOS 11/3/2004 SDV Single Stick Cost Assumes Synergy with SDV Side Mount, Standalone Cost TBD July_05 20 Atlas Evolution Summary

• Lowest Risk Growth Path for Space Exploration – Provides Crew Launch Vehicle, Cargo Launch Vehicle and In -space stages – Experienced development team with proven success record • Lowest Cost Approach for NASA – More than $10B savings does not include NASA/DoD synergy, in -space synergy savings or rate benefits • Provides substantial synergy benefits for DoD – Higher flight rate & reliability – Shared infrastructure – New capabilities

Atlas Evolution Enables Sustained Assured Access and Space Exploration

July_05 21