United Launch Alliance Advanced Development

Home , Centaur (rocket stage), RL10, Secondary payload, Star (rocket stage), Star 48, United Launch Alliance

August 28, 2007

Bernard Kutter Dwight Drefs 303-269-5538 303-269-5470 [email protected] [email protected]

ULA overview –Existing products ULA advanced programs –Secondary and multiple payloads –Large payload fairings –Lunar missions –Cargo transfer vehicles –Advanced common evolved stage –Long duration cryo storage –On-orbit refueling –Flight demonstration

50/50 joint Lockheed Martin/Boeing ownership –Responsible for all Atlas and Delta design, engineering, production, and U.S. government sales Strengthened Ability to Ensure Mission Success Assured Access via Two Independent Systems Reduced Costs –Consolidated Infrastructure –Integrated Streamlined Management Favorable Environment for Innovation

Superior Performance, Lower Costs = Mission Success

Medium Class Intermediate – Heavy Class

Delta II Delta IV Delta IV Heavy Atlas V

100% mission success is imperative

ULA is currently flying 4 upper stages

Delta 2 stage 2 Centaur Delta IV stage 2 Delta IV stage 2 1.0 mT dry 2.1 mT dry 4m diameter 5m diameter 5.9 mT propellant 21 mT propellant 2.8 mT dry 3.5 mT dry 21 mT propellant 27 mT propellant

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 Logical, Low Risk Path to Enhanced Performance

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a (in development) e LEO Payload* (t) H East and West Coast 10 Capable Potential for Common Growth Upper Stage with Atlas V 0 Current Delta IV Family Delta IV Heavy+ (6.5-m Fairing)

*Ref orbit: 407-km circular at 28.5-deg inc.

ULA IRAD investments include transportation capabilities not currently offered

NASA’s exploration program offers a very exciting opportunity to extend ULA’s core competencies –Launch –In-Space stages –Landers

Atlas Atlas Delta Delta Atlas Delta

Type-C Carrier Integrated Payload Secondary Attach Carrier (IPC) (TCC) 35 lbs ea. Mounting (SAM) Reduced-Height • NASA funded phase-1 study Dual Payload • Supports Large/Multiple SPs • Uses CalPoly pPod dispenser • 3 Payloads up to 300-lbs Attach • Used for LCROSS mission • Clampband interface Fitting (DPAF) • Payloads up to 3000-lbs Atlas • Clampband interface Atlas Atlas Delta

Existing Secondary Payload Carrier Mounting (SPC) 125 lbs ea. Brackets • Up to (4) on a C-adapter EELV Secondary Payload Aft Bulkhead Carrier Adapter (ESPA) 400 lb ea. (ABC) 100 lbs ea. • Proven on STP-1

8 Copyright © 2006 ULA. All rights reserved. Dual Spacecraft System (DSS) Payload Envelope: Low cost medium dual No DSS Plugs payload carrier 100” Dia Derived from existing flight 50” hardware Dia –2 Centaur forward adapters 50” 100” Tall –4m PLF separation bolts

Three DSS Plugs 100” Dia

DSS 50” Dia

125”175” Tall Atlas V or Delta IV

Dual Payload Carrier (DPC) is a 77ft PLF common adapter for both Atlas & Delta launch vehicles to launch two Upper Payload primary payloads on a single mission Envelope (PLE)

Lower PLE

DPC located Common DPC within 77 ft. PLF on Atlas V 5xx

63-ft PLF

Upper Payload Envelope (PLE)

Lower PLE

Common DPC DPC Located within 63-ft PLF on Delta IV Heavy

Larger payload fairings can be accommodated within current 110’ system infrastructure 6.5-m – Longer PLF’s 86-ft length – Larger diameter PLF’s 87’ 77’ Enhanced PLFs derived 14’ 68’ from current design – Delta IV heritage: 10’ to 4-m to 5-m – Flight proven heritage separation systems

4.2m 5.4m 5.4m 7m 14’ 17.8’ 17.8’ 22’

De-Orbit Numerous transportation Burn architecture options Descent Key considerations include: Lunar Orbit – Mission design Coast • Staging at LEO, TLI, LOI,… • Upper stage lunar impactor Landing Burn

– Launch vehicle Lunar Insertion Burn • Number of stages: 3 or 4 • Propellant (storable/cryogenic)

Launch Trans-Lunar Coast Low Earth Earth Orbit Orbit Insertion Burn

Earth Departure Burn Possible Delivery Points Optimal Transportation Architecture Depends on Mission Requirements

Assumptions: Legend Payload Lander dry/prop mass -MF derived from Delta 2 2nd stage -ISP = 320 -TLI: C3=-1.9 km2/sec2 401+storable lander 0.5 0.7/2.5 0.7/2.5 -2,560 m/s for LOI+Descent Stage during TLI Reference: nd 431+storable lander 1.3 0.7/3.6 Delta 2 2 stage: 1.0 / 5.9 mT Stage during TLI Star 48 0.23 / 1.9 mT Centaur 2.1 / 21 mT DIV US 4m 2.8 / 21 mT 551+storable lander 1.7 0.8/3.8 Stage after TLI DIV US 5m 3.5 / 27 mT In Work 552S+taDg2e dUuSr+insgt oTrLaI b&le d ularinndg eLrOI

2.8 0.9/5.6 A-HLV+storaSbtalege l aanftdere TrLI

In Work D-HLSVta+gDe 2a fUteSr +TsLtIo &ra dbulrein lga ndedsecrent 2.5 0.7/3.3 552+2nd CeSntatageu sr+ubst LoErOa b&le d ularinndg eLrOI 3.9 3.1/32 Stage during TLI A-HLV+Centaur derived lander 4.6 0.7/2.7 Stage during TLI & during descent HLV+2nd Centaur+storable lander

0 1 Lun2 ar Land3ed Mass4 (mT) 5 6 7 Mass (mT) ULA Provides Alternative Lunar Transportation Options

Reasonable upgrades enable long duration missions –Hours to several months using passive thermal management only

Multi-Layer Insulation (MLI) Sun shield Solar Power Adapter Thermodynamic vent system (TVS) – Vapor venting in low-g Vapor cooled shield(s) (VCS) Navigation update – Boiler + Superheat – Penetration thermal shorting (e.g. fill/feed/vent lines) Improved Thermal Control using TVS Vehicle orientation

H para-ortho conversion 2 Additional N2H4 – Increased heat capacity

Centaur Delta IV US

Upgrades enable upper stage derived landers –Landing large cryo stage vertically poses issues • Very tall stage • Requires deep throttling of RL10 Horizontal Landing Offers Advantages –Horizontal landing with auxiliary propulsion attractive –Large payload capability –Provides potential linkage to LSAM

Large tanks & hardware may Large residual H2 & O2 benefit insitu and base beneficial for ground operations External “Hot” Structure & Landing Payload/Equipment Mounts Propellant

Sidewall & Solar Power Bulkhead MLI Landing Adapter Thrusters

Potential New Market for Construction, Crew and Cargo Delivery to Low Bigelow Habitat Earth Orbit (LEO) ISS

– Service to Destinations SpaceX Dragon with Permanent Human Presence

ATV Rocketplane Kistler – ISS exists, Bigelow OV-1 Habitat in Planning Stage

Commercial LEO SpaceDev DreamChaser Transportation System HTV Consists of Two Elements: Launch Vehicle & Transfer TRANSFER VEHICLE Vehicle LAUNCH VEHICLE * Photos courtesy of NASA, Bigelow Aerospace, SpaceX, Rocketplane Kistler , SpaceDev

Cargo Delivery Vehicle o – Capability A/B/C rg Evolved From Existing a Components

/C – Structure/Propulsion: Centaur

w – Avionics/ProxOps: Orbital Express re – Reentry: IRVE & PaiDai

l C Compatible with existing,

ia flight-proven vehicles

rc Features e – Flexible performance m – Existing payload processing

m – Based on flight proven

o elements

C – Benign ascent environments – Low impact return/recovery

1 RL10

Vehicle equipment Vapor- Monocoque Al cooled Payload adapters 2 RL10 Aft thrust structure alloy tank structure forward skirt

Booster severance system Monolithic spun Aft skirt domes

4 RL10

6 RL10 H2 vent Tank interface ring Coaxial VJ H2 ducts sump Engine interface structure

Modular Design Maximizes Utility, Minimizes Risk & Cost

Developing next generation tank construction –Extending Delta’s current longitudinal FSW to circumferential and thinner gauge Aluminum alloys (0.04” to 0.1”) –Goal to implement circumferential FSW on Atlas Booster at Decatur –Goal: Reduce ACES tank weight by 2 relative to Centaur

Future Cryo-storage enhancements 0-G pressure control Cryo cooler supports indefinite storage Prelaunch subcooling Vapor cooled shield

Sun Shield (SS)

Low-conductivity adapters Settled pressure control

Vapor cooled points (VCP) Low-surface area Vacuum insulation panels (VIP)

Variable density multi-layer Common bulkhead insulations (VDMLI)

Internal vacuum feedline

Minimal penetrations Propellant positional management system (PPMS) Sump design

System Design COLD Technologies Enable passive 0.01%/day boil off

Existing Passive Technologies Allow Months On-Orbit

21 Copyright © 2006 ULA. All rights reserved. Depoyable Sun Shield Packed Enable long duration cryo storage –Applicable to stages regardless of PLF encapsulation –Deployable, light weight, reliable 2009 potential flight demonstration

Deployed

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h 5 t n i u L W 0 Pictures Credit: NASA 0EDS Propella2n0t Mass Beyo4n0d ESAS Bas6e0line (mT) 80 Fill EDS beyond ESAS baseline significantly increases lunar delivered payload – EDS is only half full in LEO for ESAS Accommodates mission delays or high cryo boil-off – Centaur experience shows boil-off variation of factor of 2 – Additional propellant launches can replenish cryo propellants Launched empty, LSAM can be much lighter improving exploration CCrryyoo TTrraannssfeferr CCaann EEnnhhaannccee EExxpplolorraatiotionn

Cryo Transfer Technology TRL Zero G Settled System Chilldown 8 8 Propellant Acquisition 3 9 Passive Long Duration Storage 5 5 Cryo Fluid Transfer Ullage & Liquid Stratification 3 9 Propellant Expulsion Efficiency 3 8 Mass Gauging 3 9 –Use of settled cryo fluid transfer builds on Pressure Control 4 9 Fluid Coupling 6 6 existing, flight proven fluid management Autonomous Rendezvous & Docking 6 6 experience Transfer System Operation 3 6 -5 Centaur CFM Flight Demo –Centaur flight demos with CFM at 10 g’s Low-G demo TE MP PATCH LOCATION Q1 Q2 Q3 Q4 -50 -30 -10 10 30 50

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N -222 O –Near term ride share can provide system I T e A -234 T S r -246 R -250 U A P

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d e d d i i M Progress S 30 min Side wall remains warm, indicating settling is effective –Dart, XSS-11 and Orbital Express recent Centaur Test Bed Cryo Transfer Demo American flight demonstrations Valve & Instrumentation Panel –CEV and COTS require AR&D for ISS Receiver Bottle

Existing or Near Term Technologies

24 Copyright © 2006 ULA. All rights reserved. Flight Demonstration Post-Flight Demonstration Opportunities Cryo Fluid Management Technologies Secondary Payloads Benefit from Flight Demonstration Mass Gauging Sun Shield – Builds Confidence in Emerging Concepts Propellant Transfer Pressure Control Vapor Cooled Points Post Flight Demonstrations Provide Inexpensive, Near Term Experience Low-G Slosh

with Promising Technologies Variable Density MLI 5,000 Vapor Cooled Shield

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7 8 8 -3 -4 9 1 2 6 7 0 7 7 0 0 8 8 8 0 2 S S -2 -4 G 0 0 0 0 0 0 0 0 0 0 1 1 L L - 0 0 2 0 0 2 2 0 0 0 0 0 P P S 2 2 2 2 2 2 2 2 2 G G O O 8 8 G 0 1 -2 4 4 1 3 9 5 R R IR 2 1 - 3 F t- 2 F 3 4 N N B - - - - S a - G - - - L P O L S P s L - SDO 2008S L L S O STP-1 2006S IC O G G r O S G O O R M R a R IR R R N N W m N B W N N D In S ULA US’s Provide Near Term Flight Demonstration Opportunities

Utilize centrifugal force & solid body rotation separating liquid/gas –Acceleration ~ 3*10-5 G’s; similar to existing flight experience Centrifugal settling reduces liquid heating –Dry walls primarily heat ullage, not liquid Enables 0-G venting using US venting experience physics –Continuous low flow venting enables vapor cooling Acceleration Liquid

Heating to Ullage ullage

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ULA Strengthens Ability to Meet Critical USG Mission Requirements –Creates Favorable Environment for Innovation Pursuing solutions for enhanced space transportation –Secondary Payloads –Lunar and Long duration missions –Evolution of current stages

Low Risk, Affordable Solutions Transportation Capability

Atlas V Launch Vehicle Family Vehicle Naming Convention: Atlas V xyz 1st Digit = x = PLF Diameter (meters) 2nd Digit = y = No. of SRBs (0 to 5) 3rd Digit = z = No. of Centaur Engines (1 or 2)

Vehicle 400 500 Heavy Series: PLF 4.2 Meter 5.4 Meter 5.5 Meter Diameter LPF Short (68’) Long (87’) EPF Med (77’) XEPF Long (87’)

No. of 0 thru 3 0 thru 5 2 LRBs Strap-Ons SRBs SRBs

No. Centaur 1 or 2 1 or 2 1 or 2 Engines The Atlas V Launch Vehicle Family Provides: • Modular, Common Element Design • 4 & 5 Meter Payload Fairings • Standard Payload Interfaces 400 500 HLV • Standard Kits for GSO

Naming Convention: Delta IV Medium + (4,2)

Vehicle class Medium

Payload Fairing (PLF) Number of Graphite 4-m PLF Diameter (meters) Epoxy Motors (GEM) (4,2) (11.7-M length) Medium +

(5,2) Delta IV PLF GEM Vehicle Class Diameter Length Medium 4-m 11.7-m - Medium + (4,2) 4-m 11.7-m 2 (5,4) Medium + (5,2) 5-m 14.3-m 2 Medium + (5,4) 5-m 14.3-m 4 Heavy 5-m 19.1-m -

Heavy 5-m PLF 5-m PLF (14.3-M length) (19.1-M length)

DSCS III A3 Aura Deep Impact New Horizons THEMIS 03/10/03 7/15/04 1/12/05 1/19/06 2/17/07 National Hellas-Sat Messenger Inmarsat 4 F-1 Astra 1KR STP-1 05/13/03 8/3/04 3/11/05 4/20/06 3/8/07 Security Launches

Rainbow 1 GPS IIR-13 NOAA-N CALIPSO/ COSMO -1 07/17/03 11/6/04 5/20/05 CloudSat 6/7/07 NASA/ 4/28/06 NOAA GOES N NRO L-30 Launches DSCS III B6 SWIFT MRO 5/24/06 6/15/07 08/29/03 11/20/04 8/12/05

NROL-22 GPS IIR-14 AMC-16 6/27/06 12/17/04 9/25/05 Phoenix 8/4/07

Heavy 1st ULA 1st Launch NROL-21 12/21/04 12/14/06