8-Conference Material - No License-0054 Input to the Steering Group of the Planetary Society Decadal Survey Medium Lift Launch Vehicle Solution 22 February 2010 Warren Frick Advanced Programs, Orbital Sciences Corporation 8-Conference Material - No License-0054 Orbital Overview • Leading Developer and Manufacturer of Small- Full Development, Production, to- Medium Class Satellites and Launch Vehicles Test and – Focused on Customer Needs, Emerging Market Areas and Innovative Solutions Operations Capabilities – Wide Spectrum of Products and Experience in Government and Commercial Markets – Provide High Performance/Reliable Systems, on Short Schedules, at Affordable Prices 3,500 Employees, State-of-the-Art Facilities • Some 835 Satellites and Launch Vehicles Built or On Contract for Customers – 730 Systems Developed, Built and Delivered From 1982 to 2009 Dulles, Virginia – 105 Systems Under Contract for Satellite Engineering, Deliveries From 2010 to 2013 Manufacturing, Test and Operations • Over $4.8 Billion Total Contract Backlog With Premier Customers • Revenues of $1.17 Billion in 2008, Aiming for !10% Annual Long-Term Growth Chandler, Arizona Launch Vehicle Engineering, • Conservative Balance Sheet, Strong Cash Manufacturing and Flow and Liquidity Test Page 2 8-Conference Material - No License-0054 Orbital Sciences Product Lines Launch Vehicles and Missile Systems Satellites and Other Space Systems Space Launch Interceptor Target Communications Scientific Other Space Vehicles Launch Vehicles Vehicles/Missiles Satellites Satellites Systems • 656 Launch Vehicles Developed, Built or Under Contract • 179 Satellites/Space Systems Developed, Built or Under Contract • 97% Mission Success Achieved Over Last 10 Years (99 • 97% Mission Success Achieved Over Last 10 Years (70 Space Systems) Vehicles) Advanced Space Programs Advanced Launch Vehicles Human Space Systems Military Satellites • 8 Major Advanced Space Systems Conceived, Prototyped or Under Contract to Develop Innovative Solutions Across All Sectors • Involve Customer- and Company-Funded R&D and Limited-Quantity Production Programs to Demonstrate New Technologies Page 3 8-Conference Material - No License-0054 Taurus ® II Medium Class Launch Vehicle Designed to provide reliability, flexibility and cost-effective access to space for medium-class payloads Two Decades… 10 Space and 8-Conference Material - No License-0054 Strategic Launch Vehicles BUILDING ON A HERITAGE OF SUCCESS • Orbital has Successfully Developed More Launch Vehicles During the Last 20 Years Than Any Other Organization • The Taurus II Launch System Leverages Orbital’s Heritage of our Highly Successful Pegasus, Taurus, and Minotaur Space Launch Vehicles, As Well As Launch Vehicles Developed for the Nation’s Missile Defense Systems • Taurus II is Being Developed, Manufactured and Launched Using Proven Management Approaches, Engineering Standards, and Manufacturing and Test Processes Common to Orbital’s Other Major Launch Vehicles Page 5 8-Conference Material - No License-0054 Taurus II Justification • Orbital had a need for a medium- capacity launch vehicle to perform space lift for the Cygnus ISS resupply space vehicle. – 8 Missions to deliver 20,000 kg cargo to the International Space Station • Delta II Launch Vehicle was not affordable and increasingly • Large performance gap between unavailable small and Intermediate class launch vehicles • Business case justified – To 600 km/Sun Sync orbit development of reliable medium- • 1200 kg maximum performance class replacement vehicle for for Minotaur IV and Taurus XL Vehicles (Small) space access • 7000 kg minimum performance – ISS resupply for Atlas V 401 and Delta IV M Vehicles (Intermediate) – LEO access – Delta 7300 to 7900 replacement – High energy science access Page 6 8-Conference Material - No License-0054 Taurus II vs. Delta II Comparisons Delta II 7320 Delta II 7920 Taurus II Taurus II E 9.5’ Fairing 10’L Fairing Height 40 m 44 m 38.2 m 38.9 m Gross Lift-Off Weight 285,000 kg 300,000 kg 162,000 kg 230,000 kg Performance to 200km 3,800 kg 5,300 kg 1905 kg 3,470 kg Sun Synch. Inclination Performance to 200 km 5,000 kg 6,900 kg 2,800 kg 5,530 kg 28.5" Inclination High Energy 1,100 kg 1,300 kg 775 kg 1,155 kg Performance (Castor 30A/ (HEUS/ Star (7425) (7925) C3 = 0 km2/sec2 Star 48) 48) Payload Envelope 3. 5 m x 7.7 m 3. 5 m x 8.7 m 2.5 m x 6.8 m 2.7 m x 7.4 m Width X Length Payload Volume 50 m3 60 m3 26 m3 38 m3 Page 7 8-Conference Material - No License-0054 Taurus II Schedule and Manifest Page 8 8-Conference Material - No License-0054 Key Access Dates • Taurus II – Risk Category 1 • No successful flights, ISO 9001 Certification, NASA Audit, Range Safety Compliance, Comprehensive Acceptance Test Results, etc. • Payload Class D Risk Tolerance (Low significance payloads) – Risk Category 2 – 1st H, 2011 • 1 Successful launch, NASA Audit, Range Safety Compliance, Comprehensive Acceptance Test Results, etc. • Payload Class C & D Risk Tolerance (Low to medium significance payloads) – Risk Category 3 – 1st H, 2013 • 3 Successful launches, NASA Audit, Range Safety Compliance, Comprehensive Acceptance Test Results, etc. • Payload Class A, B, C & D Risk Tolerance (Medium to high significance payloads) • Taurus II Enhanced – Category 3 Certification – 2nd H, 2014 • 3 Successful launches of evolved vehicle family, NASA Audit, Range Safety Compliance, Comprehensive Acceptance Test Results, etc. • Payload Class A, B, C & D Risk Tolerance Page 9 8-Conference Material - No License-0054 Taurus II Launch Vehicle Overview Payload Fairing • 3.9 meter diameter by 9.9 meters high • Composite Honeycomb core structure with Graphite-Epoxy Composite Face • Non-contaminating Frangible Rail and Ring Separation System • Cold-gas actuator/hinge fairing jettison Baseline Stage 2 system • Overall stage development and integration by Orbital • ATK CASTOR ® 30 Solid Motor with Active Thrust Vectoring • Orbital MACH avionics module • Cold-gas 3-axis Attitude Control System VEHICLE PARAMETERS Stage 1 • Overall stage development and integration by Orbital • Gross Liftoff Mass: 290,000 kg • Main engine design and production by Aerojet and Orbital • Vehicle Length: 40 m • Two AJ26-62 engines with independent thrust vectoring • Vehicle Diameter: 3.9 m • Liquid Oxygen/RP-1 fueled • Core design and verification by Yuznoye (Zenit- derived heritage) and Orbital • Core production by Yuzhmash Taurus II Core Utilizes Heritage Vendors with Large Manufacturing Capacity Page 10 8-Conference Material - No License-0054 Taurus II Heritage • To control risk and maximize reliability, Orbital chose experienced partners and subcontractors for Taurus II development – ATK – CASTOR ® 30, STAR-48 • Unparalleled in Solid Motor Development – Aerojet/SNTK – AJ-26 • Nearly 100,000 seconds of test time of heritage NK-33 engines • 200,000 including derivative NK-15 and 43 engines – Yuzhnoye/Yuzhmash – Stage 1 Core • Zenit (Sea Launch), Dnepr, Cyclone • Major subcontractors all have extensive experience – Moog – AACS – Etc. Page 11 8-Conference Material - No License-0054 Taurus II Main Systems and Suppliers Fairing and Primary Composite Structures – Applied Aerospace Structure Corp. - California Payload Separation Systems – RUAG Space AB - Sweden Attitude Control System Tanks– Ardé – New Jersey Frangible Joint Separation Attitude Control System Thrusters & Systems – Ensign Bickford Corp. TVC System– Moog – New York - Connecticut Stage 2 Castor 30 Solid Motor – Alliant Techsystems - Utah Avionics & Guidance Control Systems – Orbital Science Corp. - Arizona Stage 1 Core Structures and Fueling Systems – N.P.O. Yuzhnoye / Yuzhmash - Ukraine AJ-26-63 Main Engines – Aerojet General Corp. Main Engine Feed Lines – - California FMH Inc. - California Main Engine Thrust Vector Control System – Moog Aerospace Corp. – New York Main Engine Thrust Frame – Aft Thermal Blanket – Process Fab Inc. - California Hi Temp Corp - Texas Page 12 8-Conference Material - No License-0054 Taurus II Enhanced • Independent Team Was Created in Sep 2009 to Identify a Path to Taurus II Enhanced Performance for Jan 2013 ILC – Replaced Castor ® 30 With New 2nd Stage • Top Requirements: – Injection Orbit 200 Km Circular, 51.6 Deg from WFF – Increase payload volume by 1m, linearly – Ready for ILC Of 1/31/2013 – Utilize Existing Stage 1 and Ground Infrastructure • Top Goals Drawings are – Requirement 6500 Kg, Goal 6700 Kg conceptual and not based on Payload Performance specific solution. – Improve Injection Accuracy from Baseline Vehicle – Utilize Current Upper Stack Design as Much as Possible • Schedule Milestones – Kickoff Development Meeting January 2010 Standard 2-Stage 3 Stage Option 2 Stage Option to Meet 2013 ILC Page 13 8-Conference Material - No License-0054 Taurus II High Energy Third Stage • STAR-48 Based third stage supplements CASTOR® 30 and Enhanced Taurus second stage for high energy space access • 3-axis stabilized (non-spinning) stage baselined • Orbital developing similar STAR 48BV and STAR 37 stages for Minotaur IV+ and Minotaur V – Decades of experience developing solid-motor based stages – Recent experience with small (STAR 27) stage for NASA’s successful IBEX mission • STAR 48 has long heritage of high energy missions – Propelled fastest object mankind has ever launched • Less than two years to develop stage Page 14 Launch Vehicle High Energy 8-Conference Material - No License-0054 Performance Capabilities Launch Vehicle Performance to C3 = 0 8000 ! !"#$%&'()%* 7000 ! +#$'&%,# ! -#.#*("'), 6000 /()0*')#1')1213$45 5000 4000 3000 Performance