Taurus II Development Status of a Medium-Class Launch Vehicle for ISS Cargo and Satellite Delivery David Steffy Orbital Sciences Corporation 15 July 2008 Innovation You Can Count On™ UNCLASSIFIEDUNCLASSIFIED / /Orbital Orbital Sciences Sciences Proprietary Proprietary 1 Orbital’s Space and Strategic Launch Vehicles Pegasus XL Minotaur I Taurus XL Minotaur IV Taurus II KEI OBV Minotaur II Minotaur III Space Launch Vehicles Strategic Launch Vehicles z 172 Space and Strategic Launch Vehicles Produced During 25-Year Period ¾ 102 Vehicles Built and Delivered in Last 18 Years (1990-2008) ¾ 70 Vehicles Under Contract for Deliveries in Next 7 Years (2008-2014) z Capable of Orbital, Suborbital and Earth Escape Launches ¾ 500 kg to 6,000 kg Payloads to Low-Altitude Orbits ¾ ICBM-Class Interceptors and Long-Range Targets z Operated from 7 Launch Sites (4 CONUS, 3 Other) UNCLASSIFIED / Orbital Sciences Proprietary 2 Taurus II Program Highlights z Designed to Provide Delta II-Class Payload Performance at All-Inclusive Launch Prices of ~$65 Million With High Mission Reliability and Responsiveness ¾ Orbital Is Applying Its Well-Established Engineering, Manufacturing, Supplier Management, Mission Assurance and Program Management Capabilities to Develop, Qualify, Produce and Operate the Taurus II Vehicle ¾ Taurus II Is Based on a High-TRL Design to Minimize Development and Early- Flight Risk, While Also Using Selected Non-Traditional Suppliers and a Lean Fixed Infrastructure to Maintain Attractive Launch Costs z Designing to Provide Launch Services for a Variety of Different Missions ¾ NASA Science/Planetary and Space Station Resupply; NASA Cat. 3 Reliability ¾ DoD/IC Gapfillers, Demos, Space Superiority, and Medium-Class Missions ¾ Operationally Responsive Space ¾ Commercial LEO and GEO z Taurus II Is On Schedule for Its First Launch(es) in Late 2010 and Will Be Capable of Supporting Up to 6 Launches per Year By 2012 z Orbital and Our Partners Are Investing ∼$200 Million of Our Own Capital to Fund Taurus II Development, Support Equipment, Production Inventory and Launch Site Infrastructure Taurus II Will Be Ready to Fill the Medium-Class Satellite “Launch Gap” by 2010 UNCLASSIFIED / Orbital Sciences Proprietary 3 Taurus II Vehicle Overview Program Goals 3.9 m Fairing (Orbital) • Minimize Development NRE -- Select High TRL Components or Components Already Under Development • Minimize Recurring Costs -- Eliminated Strap-on Booster Rockets Castor 30 Stage 2 Motor • Meet or Exceed Delta II Performance Parameters -- Drove (ATK) Environments, Payload Volumes, and Performance • Minimize Launch Site Infrastructure – Use Horizontal Integration/Spartan Pad Concept • Design for High Reliability -- Use Heritage Components 3.9 m Propellant Tanks/ Stage 1 Core Vehicle Mass and Dimensions: (Yuzhnoye) • Gross Liftoff Mass: 290,000 kg • Vehicle Length: 40.5 Meters • Vehicle Diameter: 3.9 Meters • Payload Fairing Diameter: 3.9 Meters Dual LOX/RP AJ26 Engines (Aerojet) UNCLASSIFIED / Orbital Sciences Proprietary 4 Stage 1 Overview LOX/Kerosene Propulsion Using Existing AJ26 Engines • Avoids High Cost and Handling Difficulties of Solids or Strap-ons • Engines Offer High Performance with Extensive Test History • Stage Core Build on Existing Tooling with Heritage Design and Components • Constant Vehicle Configuration Throughout Atmospheric Flight UNCLASSIFIED / Orbital Sciences Proprietary 5 Vehicle Upper Stack z Composite Upper Stack Similar to Other Orbital Vehicles ¾ Typical Composite/Honeycomb Structures Produced by Orbital’s Trusted Heritage Suppliers ¾ Castor 30 Motor Developed by ATK as Shortened Castor 120 Payload Fairing ¾ Existing Avionics, Separation Systems and Payload Attitude Control Components Cone z Optional Bipropellant Orbit Raising Kit Fairing ¾ Provides Precision Injection or Additional Avionics Sep Joint Burns for Higher Orbits Cylinder z Payload Fairing Accommodations Motor Cone/ Stage 2 Fairing Ext. ¾ 3.5 m Inside Diameter Fairing Cylinder Extension 3 Sep Joint ¾ 50 m Volume Cylinder Motor S1 Sep Cone Stage 1 Joint UNCLASSIFIED / Orbital Sciences Proprietary 6 Orbital’s Avionics System Uses Flight-Proven Hardware and Software UNCLASSIFIED / Orbital Sciences Proprietary 7 Taurus II LEO Mission Performance 7000 2 COTS Reference Orbit 200 km, 51.6 ° 8. 7° 2 6000 -S ta ge 2 51.6° 3-Stage 8.7 ° 3 + -Stage 5000 5 1. 6° 2 -S ta ge S 4000 un Sync hronous 3-Stage Payload Capability (kg) Capability Payload 3000 NASA LSP Reference Capabilities Su n S ync hro nou 2000 s 2 -St age 1000 100 200 300 400 500 600 700 800 900 1000 Circular Orbit Altitude (km) UNCLASSIFIED / Orbital Sciences Proprietary 8 Wallops Flight Facility Launch Complex Liquid Fueling Horizontal Integration Medium-Class Facility Processing Facility Launch Pad (New) (New) (Taurus II, Etc.) Small-Class (Upgraded) Launch Pad (Minotaur, Etc.) Payload Processing (Existing) Facility (Bldg H-100) 7 Miles Minimum Launch Site Infrastructure Adaptable to Multiple Sites z Horizontal Processing Leverages Existing Facilities and Minimizes On-Pad Time ¾ Transport/Erect Concept Avoids a Fixed Umbilical Tower and Service Tower ¾ Inherently Better Payload Protection from Hazardous Environments z Orbital’s Standard EGSE Augmented to Control Mobile Fueling Pump Skid z Partially Relocatable Fuel/LOX/Gas Systems Minimize Standing Infrastructure and O&M Costs UNCLASSIFIED / Orbital Sciences Proprietary 9 Taurus II Ground Concept of Operations Operations Use Horizontal Processing and Minimal Pad Infrastructure z Vehicle and Payload Processed at Horizontal Integration Processing Facility z Transporter/Erector Rolls Integrated Stack to Pad z Stack Erected Hydraulically (Forces Reacted through Pad Deck) z Erector Doubles as Umbilical Mast (No Need for Mobile or Fixed Service Towers) z Pad Provides Launch Mount, Flame Trench, and Fuel/Oxidizer/Pressurant/Air Storage z One Day from Vertical to Launch UNCLASSIFIED / Orbital Sciences Proprietary 10 Taurus II Program Master Schedule Phase/Event 2007 2008 2009 2010 Qtr 1 Qtr 2 Qtr 3 Qtr 4 Qtr 1 Qtr 2 Qtr 3 Qtr 4 Qtr 1 Qtr 2 Qtr 3 Qtr 4 Qtr 1 Qtr 2 Qtr 3 Qtr 4 Approval to Proceed 4/2 Preliminary Design Phase Taurus II Vehicle PDR 2/14 Critical Design Phase CDR Schedule Margin (1 Month) Taurus II Vehicle CDR 12/15 Hardware/Software Qualification Phase Stage 1 Engine (AJ-26) Qualification Testing 10/1 Stage 2 Motor (Castor-30) Static Fire Test 5/9 Stage 1 System Qualification Testing 9/1 Launch Site Buildup and Activation 5/1 Pathfinder Vehicle Operations Flight 1 Vehicle Integration and Test Flight 1 Schedule Margin (2 Months) Flight 1 ILC (Unassigned) 10/15 Flight 2 ILC (COTS Demo) 12/15 Today (Month 15 of 45) UNCLASSIFIED / Orbital Sciences Proprietary 11 Taurus II Early-Flight Confidence z Excellent Reliability Record Reflects Conservative Engineering, Aggressive Supplier Management, and Disciplined Manufacturing/Test Processes ¾ 25 Consecutive Pegasus Launches Fully Successful Over 10-Year Period ¾ All 14 Minotaur Launches Fully Successful Over 7-Year Period ¾ All 6 OBV Launches Fully Successful Over 4-Year Period UNCLASSIFIED / Orbital Sciences Proprietary 12 Taurus II Production and Supply Assurance Plan z Vehicle Production and Launch Site Plan for First 6 Years of Operations ¾ 2010-2012: 6-7 Vehicles to Be Built and Launched Planned Missions Include 4-5 COTS/CRS, 2 Others One Launch Site Activated (Wallops Flight Facility) ¾ 2013-2015: 12-14 Vehicles to Be Built and Launched Planned Missions Include 6-7 CRS, 5-7 Others Second Launch Site Activated If Required (Vandenberg AFB or Cape Canaveral AFS) z Stage 1 Main Engine Supply (Aerojet/NDK) ¾ Orbital Purchasing 3 Flight Sets and Has Right of First Refusal on 15 More Sets (36 Engines Total) in Aerojet’s Sacramento, California Inventory ¾ Orbital and Aerojet Expect to Conclude the Purchase of an Additional 15 Flight Sets (30 Engines) from NDK’s Samara, Russia Inventory z Stage 1 Tanks, Lines and Structure Supply (Yuzhnoye/Yuzhmash) ¾ First Flight Units and Qualification Unit Now Under Contract ¾ Three-Unit U.S. Inventory to Be Established by 2011 and Maintained Thereafter UNCLASSIFIED / Orbital Sciences Proprietary 13 Wallops in 2011: From the Eastern Shore to ISS Horizontal Integration & Processing Facility H-100 (WFF Main Base) Cygnus/Cargo Module Processing at WFF Taurus II Launch from Pad 0A Cygnus Rendezvous With ISS UNCLASSIFIED / Orbital Sciences Proprietary 14 Contact Information David Steffy Senior Vice President Advanced Program Group (703) 433-6057 [email protected] Kurt Eberly Deputy Program Director Launch Systems Group (703) 433-6024 [email protected] Orbital Sciences Corporation 21839 Atlantic Blvd Dulles VA, 20166 UNCLASSIFIED / Orbital Sciences Proprietary 15.