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Minotaur I Fact Sheet

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Minotaur I Fact Sheet FACT SHEET Innovation You Can Count OnTM Minotaur I Space Launch Vehicle MightySAT II.1 JAWSAT – Jan 2000 – Jul 2000 XSS-11 – Apr 2005 STP-R1 – Sep 2005 COSMIC – Apr 2006 TacSat-2 – Dec 2006 Minotaur I Has a Demonstrated Success Record and Flight-Proven Systems The Minotaur I Space Launch Vehicle 754.7 The Minotaur I Space Launch Vehicle (SLV) provides a responsive, SPACECRAFT reliable, and cost-effective launch solution for U.S. Government-sponsored FAIRING spacecraft. It builds on a long background of dependable launch systems AVIONICS and has a demonstrated successful history over its initial and subsequent PAYLOAD I/F ASSEMBLY launches. The Minotaur I SLV uses residual Minuteman II first and second 650.15 stage rocket motors along with the upper two stages shared with Orbital’s ORION 38 FAIRING SEP 580.85 Pegasus XL and Taurus XL commercial SLVs. The combination of 3/4 INTERSTAGE decommissioned ICBM motors with commercial boosters and state-of-the- 50.0 IN. DIA ORION 50XL art hardware is one of Orbital’s unique strengths from experience spanning S2/S3 SEP several decades. 2/3 INTERSTAGE 494.75 The Minotaur family of launch vehicles are provided via the Orbital/ 441.05 52.0 IN. DIA Suborbital Program 2 (OSP-2) and managed by the U.S. Air Force Space SR19 and Missile Systems Center (SMC), Space Development and Test Wing’s (SDTW) 3rd Space Test Squadron (3 STS) located at Kirtland AFB, NM. MM 1/2 INTERSTAGE 340.52 Features: S1/S2 SEP • Full spacecraft integration support, including mission management, 289.50 274.43 spacecraft interface support (power, telemetry, sequencing, attitude M55 control, and deployment), through launch operations and post-launch performance evaluation. • Standard 18 month mission response including mission integration and launch by Orbital’s uniquely experienced team 65.76 IN. DIA • Responsive launch solutions from 6 months to a few hours available • Mission success is ensured by mature systems and processes - Orbital’s rigorous mission assurance program 51.79 (Dimensions in Inches) - Full Government insight and independent assessment 0.0 • Multiple spaceport launch capability (California, Florida, Alaska, Mid- Atlantic) using portable ground support equipment Minotaur I Space Launch Vehicle – Ready to Launch Minotaur I Specifications Performance: • Spacecraft mass-to-orbit of up to 580 kg to LEO (28.5 deg, 185 km) 3.843 m 0.787 m (151.5 in.) (31.0 in.) 0.576 m • Typical orbit accuracy of better than ±5 km insertion apse, 2.23 m (22.7 in.) (87.8 in.) 3.335 m ±35 km non-insertion apse, and ±0.1 deg inclination (3- AVAILABLE (131.3 in.) ENVELOPE sigma values) (DYNAMIC) 0.899 m • Optional enhanced insertion accuracy better than 5 km in 1.20 m (35.4 in.) altitude and ±0.05 deg inclination (3-sigma values) (47.3 in.) AVAILABLE 2.035 m • Cold gas attitude control system readily accomodates a ENVELOPE (80.1 in.) (DYNAMIC) variety of spacecraft mission requirements, including precise separation pointing and post-boost maneuvers 1.19 m (47.0 in.) 0 INTERFACE PLANE 1.39 m (54.7 in.) 1.27 m INTERFACE PLANE (50.0 in.) 0.0 1.55 m (61.0 in.) 2000 NOTE: Standard 1.27 m (50 in.) Fairing Envelope Optional 1.55 m (61 in.) Fairing Envelope 1. Payload Mass includes 1800 Adapter Cone, Separation System and Other Payload Accommodations: 1600 Mission-Specific Hardware. • Standard 1.27 m (50 in.) dia. spacecraft fairing (Pegasus heritage design) • Optional 1.55 m (61 in.) dia. spacecraft fairing for larger and/or multiple 1400 spacecraft missions • Mission-specific fairing access doors for spacecraft support 1200 • Well-defined launch environments validated with flight data • Various flight-proven spacecraft separation systems available, including 1000 low-shock designs Apogee (km) CCAS • Thermally controlled fairing volume with standard Class M6.5 (100k) 28.5° 800 cleanliness WFF 38° - Optional Class M5.5 (10k) cleanliness 600 VAFB - Optional spacecraft nitrogen purge 72° 400 200 VAFB Sun-Synch Kodiak 64° 0 0 100 200 300 400 500 600 Payload (kg) Performance to Orbit Is Flight-Verified and Best in Class Simplified Horizontal Payload Integration for Single and Multiple Spacecraft Point of Contact: Program Office: For Technical Details, Please Contact Us At: Additional information should be obtained from the USAF OSP Office F Phone: 480.814.6566 USAF SMC Space Development and Test Wing (SDTW) . AIR ORC .S E U • 3rd Space Test Squadron (3 STS) • R E-mail: [email protected] S C L G P Website: www.orbital.com 3548 Aberdeen Avenue S.E. N Kirtland AFB, NM 87117-5778 Orbital Suborbital Program O r n b i io t t 505.846.5911 505.846.6489 a a l S r ci po ences Cor MINOTAUR 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 BR06003b.
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