ORS-3 I MISSION OVERVIEW

Provided by: Orbital Sciences Corporation November 2013 Launch Systems Group

Minotaur I ORS-3 Mission Highlights  LV:

 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 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

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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

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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

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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

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Minotaur I – 4 Missions – 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

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 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

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