FACT SHEET Innovation You Can Count OnTM Minotaur I Space Launch Vehicle JAWSAT – Jan 2000 MightySAT II.1 – Jul XSS-11 – Apr 2005 STP-R1 – Sep 2005 COSMIC – Apr 2006 Success on First Five Missions The Minotaur I Space Launch Vehicle 754.7 The Minotaur I Space Launch Vehicle (SLV) provides a responsive, PAYLOAD FAIRING reliable, and cost-effective launch solution for U.S. Government sponsored spacecraft. In addition to a demonstrated successful history AVIONICS PAYLOAD I/F over its initial and subsequent launches, it builds on a long background ASSEMBLY 650.15 of dependable launch systems. The Minotaur I uses residual Minuteman ORION 38 FAIRING SEP 580.85 II first and second stages in combination with the upper two stages 3/4 INTERSTAGE 50.0 IN. DIA shared with Orbital’s Pegasus XL and Taurus XL commercial SLVs. ORION 50XL The Minotaur family of launch vehicles is provided via the Orbital/ S2/S3 SEP 2/3 INTERSTAGE 494.75 Suborbital Program 2 (OSP-2) of the U.S. Air Force Space and Missile Systems Center (SMC) Rocket System Launch Program (RSLP). 441.05 52.0 IN. DIA SR19 Features: MM 1/2 • Inertially guided four stage solid rocket propulsion INTERSTAGE 340.52 S1/S2 SEP • Flight-proven systems with demonstrated success record 289.50 274.43 M55 • Multiple spaceport launch capability (California, Florida, Alaska, Virginia) using portable ground support equipment • Full payload integration support including mission management, spacecraft interface support (power, telemetry, sequencing, attitude 65.76 IN. DIA control, and deployment), and launch operations • Standard 18 month mission response including payload integration 51.79 and launch by Orbital’s experienced launch crews (Dimensions in Inches) • Responsive launch solutions from 6 months to 48 hours available 0.0 Minotaur I Space Launch Vehicle Minotaur I Specifications Performance: • Flight-verified system performance • Proven secondary payload capability 151.5 31.0 • Adaptable to a variety of payloads and orbital requirements 87.8 22.7 with typical accuracy of 33.4 nm (3s), 0±0.1 deg inclination (3s) AVAILABLE 131.3 • Optional Soft Ride for Small Satellites (SRSS) to mitigate flight ENVELOPE dynamics environments (DYNAMIC) • Available optional enhancements include: 47.3 35.4 - Insertion accuracy of <10 nm (3s) inclinations <0.05 deg (3s) AVAILABLE - Conditioned air (Class 10K), temperature and humidity 80.1 ENVELOPE control and nitrogen purge (DYNAMIC) - Additional payload access panels 47.0 0 INTERFACE PLANE 54.7 50.0 2000 INTERFACE PLANE NOTE: 0.0 1. Payload Mass includes 1800 Adapter Cone, Separation System and Other 1600 Mission-Specific Hardware. Standard 50” Fairing Optional 61” Fairing 1400 Payload Accommodations: • Standard 50 in. Pegasus-design payload fairing 1200 • Optional 61 in. fairing for larger or multiple payload missions 1000 • Thermally controlled fairing volume with Class 100K standard cleanliness Apogee (km) CCAS • Well defined launch environments 800 28.5° WFF • Variety of proven payload separation systems available 38° 600 VAFB 72° 400 200 VAFB Sun-Synch Kodiak 64° 0 0 100 200 300 400 500 600 Payload (kg) Minotaur I Payload Capability Simplified Horizontal Payload Integration Point of Contact: Program Office: For Technical Details, Please Contact Us At: Additional information should be obtained from the USAF OSP Office Phone: 480.814.6566 USAF SMC Space Development & Test Wing E-mail: [email protected] Rocket System Launch Program (RSLP) Website: www.orbital.com 3548 Aberdeen Avenue S.E. Kirtland AFB, NM 87117-5778 (505) 846-8957 FAX: (505) 846-1349 Orbital Sciences Corporation Launch Systems Group 3380 South Price Road Chandler, Arizona 85248 Innovation You Can Count OnTM © 2006 Orbital Sciences Corporation www.orbital.com BR06003.