United Launch Alliance Advanced Development August 28, 2007 Bernard Kutter Dwight Drefs 303-269-5538 303-269-5470 [email protected] [email protected] Copyright © 2006 ULA. All rights reserved. Agenda ! 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 1 Copyright © 2006 ULA. All rights reserved. ULA Overview ! 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 2 Copyright © 2006 ULA. All rights reserved. Launch Vehicle Products Medium Class Intermediate – Heavy Class Delta II Delta IV Delta IV Heavy Atlas V 100% mission success is imperative 3 Copyright © 2006 ULA. All rights reserved. ULA Upper Stages ! 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 4 Copyright © 2006 ULA. All rights reserved. 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 Logical, Low Risk Path to Enhanced Performance 5 Copyright © 2006 ULA. All rights reserved. Delta Evolution 50 s ) t 4 n e , ) ) e 5 d ! 2 Double the Payload ( 2 , a , m e r 4 5 + m e ( Capability ( d 40 g u c M a i p + + n r d u a ! M g Up to 6.5-m Diameter M e e h s p A M g n u Fairing s M 8 A a e 6 t e E M 8 - r s g 30 6 G E ! s e Up to 85-ft Length Fairing S - A a d h t G 6 R n M 8 S t s 2 6 E o 6 R + + ! - Existing Infrastructure d ) G n A S + + + + k 2 8 r 6 R ! Minor Pad Modifications 6 o - + + + w S 20 - ! Existing RS-68A y R n i v ( + 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. 6 Copyright © 2006 ULA. All rights reserved. ULA Advanced Programs ! 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 7 Copyright © 2006 ULA. All rights reserved. Secondary Payload Options 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 9 Copyright © 2006 ULA. All rights reserved. Common DPC Configuration on Atlas ! 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 10 Copyright © 2006 ULA. All rights reserved. Common DPC Configuration on Delta 63-ft PLF Upper Payload Envelope (PLE) Lower PLE Common DPC DPC Located within 63-ft PLF on Delta IV Heavy 11 Copyright © 2006 ULA. All rights reserved. Larger Payload Fairings ! 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’ 12 Copyright © 2006 ULA. All rights reserved. Lunar Missions 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 13 Copyright © 2006 ULA. All rights reserved. LPRP Possible Launch Options 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 14 Copyright © 2006 ULA. All rights reserved. Long Duration US Operations ! 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 15 Copyright © 2006 ULA. All rights reserved. Large US Derived Landers ! 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 16 Copyright © 2006 ULA. All rights reserved. Commercial LEO Delivery ! 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 17 Copyright © 2006 ULA. All rights reserved. ARCTUS: Astrotech Research & Conventional Technology Utilization Spacecraft ! 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 18 Copyright © 2006 ULA. All rights reserved. Advanced Common Evolved Stage (ACES) 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 19 Copyright © 2006 ULA. All rights reserved. Friction Stir Weld ! 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 20 Copyright © 2006 ULA.