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Ors-3 Minotaur I Mission Overview

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Ors-3 Minotaur I Mission Overview ORS-3 MINOTAUR I MISSION OVERVIEW Provided by: Orbital Sciences Corporation November 2013 Launch Systems Group Minotaur I ORS-3 Mission Highlights LV: Minotaur I Launch Site: Wallops Flight Facility, VA Mission Orbit 500 km x 500 km, 40.5 inclination Mission Objectives Launch the Integrated Payload Stack (IPS) into a Circular Orbit for the Operationally Responsive Space (ORS) Office Deployment of STPSat-3 Satellite into a Circular Orbit for the Space Test Program (STP) Office Perform Collision Avoidance Maneuver following separation of the STPSat-3 Release 28 CubeSats from Two Integrated Loadpath CubeStack Structures (4, 6U NASA and 8, 3U Cal Poly PPOD’s Dispensers) Minotaur Launch Vehicle Background 25th Overall Minotaur Launch 11th Minotaur I Launch Overall 5th Minotaur I from Wallops USE, DUPLICATION AND DISCLOSURE OF THIS INFORMATION IS RESTRICTED ON THE TITLE PAGE. WARNING: Contains "Technical Data" as defined in the ITAR TM-23897 Page 2 Minotaur I Vehicle Configuration Overview USE, DUPLICATION AND DISCLOSURE OF THIS INFORMATION IS RESTRICTED ON THE TITLE PAGE. WARNING: Contains "Technical Data" as defined in the ITAR TM-23897 Page 3 ORS-3 Mission Trajectory and Timeline 400.68 kg Time Latitude Longitude Altitude Velocity Event (sec) (deg) (deg) (km) Range (km) (km/s) 1 S1 Ignition 0.00 37.83 -75.49 -0.01 0.00 0.00 2 Pitch Down 2.50 37.83 -75.49 0.02 0.00 0.03 3 Max Dynp 37.21 37.82 -75.43 10.65 5.38 0.74 4 S1SEP/S2IGN 61.36 37.78 -75.24 32.88 22.43 1.46 5 S2 Skirt SEP 77.90 37.74 -75.06 52.06 39.73 1.70 6 S2 Separation 133.43 37.49 -73.94 124.22 141.78 2.71 7 S3 Ignition 135.53 37.48 -73.89 126.79 146.77 2.70 8 Fairing SEP 145.74 37.41 -73.62 138.99 171.81 2.86 9 S3 Burnout 209.63 36.76 -70.99 224.05 416.30 5.57 10 S3 Separation 536.97 31.03 -55.07 503.74 2017.71 5.11 11 S4 Ignition 547.97 30.80 -54.59 505.54 2069.78 5.11 12 S4 Burnout 614.17 29.23 -51.17 507.75 2442.97 7.23 13 Payload SEP 734.05 25.28 -44.37 507.07 3245.63 7.23 - IPS Sequencer Init 742.05 25.00 -43.94 507.03 3299.21 7.23 - CCAM1 884.06 19.86 -36.52 506.23 4250.38 7.23 CubeSat Wafer #1 - Deployment Start 1189.05 7.81 -22.14 504.96 6316.50 7.23 CubeSat Wafer #2 - Deployment Start 1339.05 1.64 -15.49 504.69 6630.00 7.24 - CCAM2 1554.06 -7.24 -5.99 504.81 8739.70 7.24 - RCS Gas Depletion 1744.06 -14.89 2.73 505.36 10012.96 7.24 - End of Mission 1844.06 -18.77 7.57 505.77 10680.62 7.24 USE, DUPLICATION AND DISCLOSURE OF THIS INFORMATION IS RESTRICTED ON THE TITLE PAGE. WARNING: Contains "Technical Data" as defined in the ITAR TM-23897 Page 4 Nominal Trajectory – Ground Track USE, DUPLICATION AND DISCLOSURE OF THIS INFORMATION IS RESTRICTED ON THE TITLE PAGE. WARNING: Contains "Technical Data" as defined in the ITAR TM-23897 Page 5 Minotaur Family of Space Launch Vehicles Configuration and Performance Overview TM-23897 Page 6 Minotaur Space Launch Vehicles Overview MINOTAUR SPACE LAUNCH VEHICLES Designed to provide reliability, flexibility and cost-effective access to space for government sponsored payloads USE, DUPLICATION AND DISCLOSURE OF THIS INFORMATION IS RESTRICTED ON THE TITLE PAGE. WARNING: Contains "Technical Data" as defined in the ITAR TM-23897 Page 7 Orbital Suborbital Program (OSP) Organization US Government Customer/ Sponsored Spacecraft USAF SMC SD Launch Systems Division (SMC/SDL) SMC/SDL Technical and Ops Support Minotaur I Family Minotaur I V, V, and VI Minuteman - based Peacekeeper - based Launch Vehicles Launch Vehicles Commonality • Avionics • GSE • Subsystems • Processes USE, DUPLICATION AND DISCLOSURE OF THIS INFORMATION IS RESTRICTED ON THE TITLE PAGE. WARNING: Contains "Technical Data" as defined in the ITAR TM-23897 Page 8 Minotaur Launch Vehicle System Features Provides Substantial Payload Performance into a Variety of Low Minotaur I Minotaur IV Inclination Low-Earth Orbits (LEO), Sun-synchronous, and Intermediate Transfer Orbits 1.27 to 2.3 Meter Fairings Accommodate a Range of Payloads Streamlined Vehicle/Payload Integration and Testing via Simplified Avionics Interfaces and Payload Encapsulation Incorporates Proven Government and Commercial Solid Propulsion Systems 24 Successful Missions with Multiple Configurations from 2000 through 2013 Launch Availability from Existing Ranges or Austere Sites Accommodates Low or High Inclination Orbits Minotaur I Minotaur IV Minotaur austere approach to operations requires minimal pad infrastructure and solid boosters significantly improve launch responsiveness and minimizes launch pad integration timelines USE, DUPLICATION AND DISCLOSURE OF THIS INFORMATION IS RESTRICTED ON THE TITLE PAGE. WARNING: Contains "Technical Data" as defined in the ITAR TM-23897 Page 9 Minotaur Launch Vehicle Launch Sites Minotaur I – 4 Missions Minotaur V – 1 Mission Minotaur IV – 2 Missions Minotaur I Planned – 1 Mission Pad infrastructure In Place to Support Minotaur Missions Minotaur I – 6 Missions Minotaur II – 8 Missions Minotaur IV – 3 Missions USE, DUPLICATION AND DISCLOSURE OF THIS INFORMATION IS RESTRICTED ON THE TITLE PAGE. WARNING: Contains "Technical Data" as defined in the ITAR TM-23897 Page 10 Minotaur Family of Launch Vehicles USE, DUPLICATION AND DISCLOSURE OF THIS INFORMATION IS RESTRICTED ON THE TITLE PAGE. WARNING: Contains "Technical Data" as defined in the ITAR TM-23897 Page 11 Minotaur Summary Minotaur Vehicles Build on Highly Successful Legacies Minotaur I and II: 18 Successful Launches Minotaur I TacSat-2 - WFF Minotaur IV Family: 6 Successful Launches − Including Minotaur IV-Lite, IV, IV with MPAF, IV+, and V Configurations Long Term Proven Reliability of Minuteman and PK Boosters Extensive Flight Heritage of Software, Avionics, and Structures Qualified Range Safety Components Allow Minotaur to Launch from Any US Launch Site Minotaur Maximizes Use of Flight-Proven Components with Significant Heritage and Commonality Across All Minotaur Vehicles to Minimize Risk Demonstrated Flexible Solutions to Meet the Mission-Tailored Needs of a Variety of Customers Minotaur IV Multi-Payload Adapters and Dual Orbits SBSS - VAFB Mission Specific Guidance Schemes Complex and Challenging Mission Scenarios Mission-Unique Structures, Stages, Sep Systems, and Avionics Minotaur Launch Vehicles Provide Reliable, Flexible, and Responsive Launch Capability USE, DUPLICATION AND DISCLOSURE OF THIS INFORMATION IS RESTRICTED ON THE TITLE PAGE. WARNING: Contains "Technical Data" as defined in the ITAR TM-23897 Page 12 .
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