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 UNCLASSIFIED / / Orbital Sciences 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 172 Space and Strategic Launch Vehicles Produced During 25-Year Period 102 Vehicles Built and Delivered in Last 18 Years (1990-2008) 70 Vehicles Under Contract for Deliveries in Next 7 Years (2008-2014) Capable of Orbital, Suborbital and Earth Escape Launches 500 kg to 6,000 kg Payloads to Low-Altitude Orbits ICBM-Class Interceptors and Long-Range Targets Operated from 7 Launch Sites (4 CONUS, 3 Other) 2
Taurus II Program Highlights Designed to Provide Delta II-Class Payload Performance at All-Inclusive Launch Prices of ~$65 Million With High Mission Reliability and Responsiveness 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 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 Designing to Provide Launch Services for a Variety of Different Missions NASA Science/Planetary and Space Station Resupply; NASA Cat. 3 Reliability DoD/IC Gapfillers, Demos, Space Superiority, and Medium-Class Missions Operationally Responsive Space Commercial LEO and GEO 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 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 3
Taurus II Vehicle Overview Program Goals Minimize Development NRE -- Select High TRL Components or Components Already Under Development Minimize Recurring Costs -- Eliminated Strap-on Booster Rockets Meet or Exceed Delta II Performance Parameters -- Drove 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 Fairing (Orbital) Castor 30 Stage 2 Motor (ATK) Vehicle Mass and Dimensions: Gross Liftoff Mass: 290,000 kg Vehicle Length: 40.5 Meters Vehicle Diameter: 3.9 Meters Payload Fairing Diameter: 3.9 Meters 3.9 m Propellant Tanks/ Stage 1 Core (Yuzhnoye) Dual LOX/RP AJ26 Engines (Aerojet) 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 5
Vehicle Upper Stack Composite Upper Stack Similar to Other Orbital Vehicles Typical Composite/Honeycomb Structures Produced by Orbital s Trusted Heritage Suppliers Castor 30 Motor Developed by ATK as Shortened Castor 120 Existing Avionics, Separation Systems and Attitude Control Components Payload Fairing Payload Cone Optional Bipropellant Orbit Raising Kit Provides Precision Injection or Additional Burns for Higher Orbits Avionics Cylinder Fairing Sep Joint Payload Fairing Accommodations 3.5 m Inside Diameter 50 m 3 Volume Fairing Extension Cylinder Stage 2 Motor Cone/ Fairing Ext. Cylinder Sep Joint Motor Cone Stage 1 S1 Sep Joint 6
Orbital s Avionics System Uses Flight-Proven Hardware and Software 7
Taurus II LEO Mission Performance 7000 6000 28.7 2-Stage COTS Reference Orbit 200 km, 51.6 5000 + 51.6 3-Stage 51.6 2-Stage 28.7 3-Stage Payload Capability (kg) 4000 Sun Synchronous 3-Stage 3000 NASA LSP Reference Capabilities 2000 Sun Synchronous 2-Stage 1000 100 200 300 400 500 600 700 800 900 1000 Circular Orbit Altitude (km) 8
Wallops Flight Facility Launch Complex Small-Class Launch Pad (Minotaur, Etc.) (Existing) Liquid Fueling Facility (New) Horizontal Integration Processing Facility (New) Medium-Class Launch Pad (Taurus II, Etc.) (Upgraded) Payload Processing Facility (Bldg H-100) 7 Miles Minimum Launch Site Infrastructure Adaptable to Multiple Sites Horizontal Processing Leverages Existing Facilities and Minimizes On-Pad Time Transport/Erect Concept Avoids a Fixed Umbilical Tower and Service Tower Inherently Better Payload Protection from Hazardous Environments Orbital s Standard EGSE Augmented to Control Mobile Fueling Pump Skid Partially Relocatable Fuel/LOX/Gas Systems Minimize Standing Infrastructure and O&M Costs 9
Taurus II Ground Concept of Operations Operations Use Horizontal Processing and Minimal Pad Infrastructure Vehicle and Payload Processed at Horizontal Integration Processing Facility Transporter/Erector Rolls Integrated Stack to Pad Stack Erected Hydraulically (Forces Reacted through Pad Deck) Erector Doubles as Umbilical Mast (No Need for Mobile or Fixed Service Towers) Pad Provides Launch Mount, Flame Trench, and Fuel/Oxidizer/Pressurant/Air Storage One Day from Vertical to Launch 10
Taurus II Program Master Schedule Phase/Event Approval to Proceed Preliminary Design Phase Taurus II Vehicle PDR Critical Design Phase CDR Schedule Margin (1 Month) Taurus II Vehicle CDR Hardware/Software Qualification Phase Stage 1 Engine (AJ-26) Qualification Testing Stage 2 Motor (Castor-30) Static Fire Test Stage 1 System Qualification Testing 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 4/2 2/14 12/15 5/9 10/1 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) Flight 2 ILC (COTS Demo) 10/15 12/15 Today (Month 15 of 45) 11
Taurus II Early-Flight Confidence Excellent Reliability Record Reflects Conservative Engineering, Aggressive Supplier Management, and Disciplined Manufacturing/Test Processes 25 Consecutive Pegasus Launches Fully Successful Over 10-Year Period All 14 Minotaur Launches Fully Successful Over 7-Year Period All 6 OBV Launches Fully Successful Over 4-Year Period 12
Taurus II Production and Supply Assurance Plan Vehicle Production and Launch Site Plan for First 6 Years of Operations 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) 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) Stage 1 Main Engine Supply (Aerojet/NDK) Orbital Purchasing 3 Flight Sets and Has Right of First Refusal on 15 More Sets (36 Engines Total) in Aerojet s Sacramento, California Inventory Orbital and Aerojet Expect to Conclude the Purchase of an Additional 15 Flight Sets (30 Engines) from NDK s Samara, Russia Inventory Stage 1 Tanks, Lines and Structure Supply (Yuzhnoye/Yuzhmash) First Flight Units and Qualification Unit Now Under Contract Three-Unit U.S. Inventory to Be Established by 2011 and Maintained Thereafter 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 14
Contact Information David Steffy Senior Vice President Advanced Program Group (703) 433-6057 steffy.david@orbital.com Kurt Eberly Deputy Program Director Launch Systems Group (703) 433-6024 eberly.kurt@orbital.com Orbital Sciences Corporation 21839 Atlantic Blvd Dulles VA, 20166 15