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Antares Test Launch “A-ONE Mission” Overview Briefing April 17, 2013 JFS-3/25/13 1 © 2013 Orbital Sciences Corporation. All Rights Reserved. A-ONE Mission Overview Primary Objective Conduct a Test Launch of the Antares Launch Vehicle to Reduce Risk and Improve the Probability of Success for the COTS Demonstration Mission and Cargo Delivery to the ISS Secondary Objectives Perform Payload Pathfinders where Practical Collect Payload Environments and Vehicle Data During Flight Fly Secondary Payloads Mission Approach Define and Implement the Test Launch (A-ONE) to be Representative of the COTS Demonstration Mission (Orb D1) − Launch Vehicle Configuration − Cygnus Simulator Mass Properties, Volume and Mechanical Interfaces − Orbital Parameters − Integration and Launch Operations JFS-3/25/13 © 2013 Orbital Sciences Corporation. All Rights Reserved. 2 A-ONE Mission Summary Launch Vehicle – Antares 110 Configuration Booster with Dual AJ-26 Engines CASTOR 30 Solid Motor Second Stage No Third Stage Space Vehicle - Cygnus Mass Simulator Launch Site – MARS Spaceport Pad 0A, Wallops Island, Va. Launch Range – NASA Wallops Flight Facility Launch Window – 1700hrs-2000hrs EDT Target Orbit – Altitude 250 km x 303 km, Inclination 51.64O Payload Separation Time – T+ 603 Seconds End of Mission (EOM) – T+1124 Sec 3 JFS-3/25/13 © 2013 Orbital Sciences Corporation. All Rights Reserved. Antares Designed to Provide Versatile, Cost-effective PAYLOAD FAIRING • 3.9 meter diameter by 9.9 meter envelope Access to Space for • Composite Construction • Non-contaminating Separation Systems Medium-Class Payloads STAGE 2 • ATK CASTOR® 30/30B/30XL Solid Motor with Currently Under Contract Active Thrust Vectoring • Orbital MACH avionics module to Support 10 NASA • Cold-gas 3-axis Attitude Control System International Space Station (ISS) Re-supply Missions STAGE 1 On-Ramped to NASA • Liquid Oxygen/RP-1 fueled NLS-II Contract • Two AJ26 engines with independent thrust vectoring • 3.9 meter booster derived from On-Ramped to USAF heritage Zenit design OSP-3 Contract VEHICLE PARAMETERS • Gross Liftoff Mass: 290,000 kg EELV New Entrant • Vehicle Length: 40 m • Vehicle Diameter: 3.9 m Statement of Intent Accepted • Mass to ISS Orbit: 5000 kg Baseline by USAF 6265 kg Enhanced 4/1/13-jfs 4 © 2013 Orbital Sciences Corporation. All Rights Reserved. Antares Main Systems Suppliers Medium-Lift Composite Structures Performance Payload Separation Utilizing Largely System Proven Elements From Heritage, World-Class ® Suppliers Avionics CASTOR 30 Solid Motor Thrust Vector Control Systems Frangible Separation Systems Booster Structures and Systems AJ-26 Main Engines 3/13-jfs 5 © 2013 Orbital Sciences Corporation. All Rights Reserved. Orbital Maximizes the Use of Core Systems Across Product Lines © 2013 Orbital Sciences Corporation. All Rights Reserved. 6 Antares Launch Vehicle Primary Subsystems Booster Second Stage Payload Accommodations Booster Production and Assembly in Yuzhmash Factory CASTOR 30 Motor Qualification Test Payload Fairing Second Stage Integration AJ-26 Engine Avionics Main Engine Section & TVC And System Payload Adapter RUAG 2624VS Separation System JFS-3/29/13 © 2013 Orbital Sciences Corporation. All Rights Reserved. 7 Path to Antares Initial Launch Capability Test Stand Stennis Test Test 100% Complete 100% Complete Test Engine Flight Engine Facilities Demo ATRR Comp. Engine Test Delivery Delivery & Inst. 26 - AJ 100% Complete 100% Complete 100% Complete 100% Complete 100% Complete Dwg Release Inter-Stage Bay Test Article Qual Tests 5K / 7K Test Core First Flight Unit & Fab Liquid Oxygen Tank Core Systems Inter- Tank Bay Kerosene Tank Stage Main Aft Bay Engine System st 1 100% Complete 100% Complete 100% Complete 100% Complete 100% Complete ILV Assy & HIF Pad Site Activation 5000/7000 Tests Roll-out site Launch 100% Complete 100% Complete 100% Complete 2/22/2013 w/o 4/8/13 Static Fire US Qual Tests Fairing Qual First flight units ILC 2nd 2nd stage stage 100% Complete and PLA and 100% Complete 100% Complete 100% Complete JFS-3/25/13 © 2013 Orbital Sciences Corporation. All Rights Reserved. 8 Test Launch Vehicle Processing JFS-3/29/13 9 © 2013 Orbital Sciences Corporation. All Rights Reserved. Completed Vehicle at the HIF 10 © 2013 Orbital Sciences Corporation. All Rights Reserved. Completed Vehicle Roll Out 11 12 Cygnus Mass Simulator Physical Properties Height = 199.25” Diameter = 114” Mass = 8377.6 lbs (3800 kg) Instrumentation 22 Accelerometers 2 Microphones 12 Digital Thermometers 24 Thermocouples 12 Strain Gages JFS-3/25/13 13 © 2013 Orbital Sciences Corporation. All Rights Reserved. Secondary Payloads Secondary Payload provider for the Antares Test mission is Spaceflight Services http://www.spaceflightservices.com/Services Payloads manifested are: 3U ISIPOD – NASA Ames Research Center − Three 1U Phone Sat Spacecraft ◦ “Alexander, Graham, Bell” − 1.124 kg each, Lithium battery 3U ISIPOD – Commercial Customer − Dove 1 (One 3U Spacecraft) Neither payload contains a propulsive system Anticipated time in orbit 2 weeks to 1 month Purpose – Demonstrate the Use of Smart Phones as Avionics in Cube Sats JFS-3/29/13 14 © 2013 Orbital Sciences Corporation. All Rights Reserved. Wallops Flight Facility Established in 1945 by the National Advisory Committee for Aeronautics, as a Center for Aeronautic Research. NASA's Principal Facility for Management and Implementation of Suborbital Research Programs. WFF is Ideal for Providing Equatorial Access for Low Earth Orbit Insertion. WFF Offers a Wide Array of Launch Vehicle Trajectory Options. The Coastline of Wallops Island is Oriented Such that a Launch Azimuth of 135° is Perpendicular to the Shoreline. Launch Azimuths Between 90° and 160° can be Accommodated Depending on Impact Ranges. For Most Orbital Vehicles, this Translates into Orbital Inclinations Between 38° and Approximately 60° Trajectory Options Outside of these Launch Azimuths, Including Polar and Sun-Synchronous Orbits, may be Achieved by In-Flight Azimuth Maneuvers © 2013 Orbital Sciences Corporation. All Rights Reserved. 15 Antares Wallops Footprint H-100 Mainland Cargo Processing V-55 Payload Fueling Facility H-100 Cargo Processing Facility Horizontal Integration Facility (HIF) 8.53 Miles Pad 0A V-55 2.46 Miles Payload Fueling HIF 1.1 Miles Pad 0A Liquid Fueling Facility JFS-2/8/13 © 2013 Orbital Sciences Corporation. All Rights Reserved. 16 Horizontal Integration Facility JFS-2/8/13 17 © 2013 Orbital Sciences Corporation. All Rights Reserved. Pad OA Overview JFS-3/28/13 © 2013 Orbital Sciences Corporation. All Rights Reserved. 18 Pad OA JfS 3/39/13 19 © 2013 Orbital Sciences Corporation. All Rights Reserved. Launch Countdown Timeline L-08H 00M: Call to stations L-07H 30M: Voice checks L-07H 00M: Range and facility set up L-06H 30M: Pad clear L-06H 00M: OCCS sequencer initiation/warm helium charging L-05H 50M: Vehicle power up and systems checks L-03H 40M: 15 minute hold L-03H 00M: Start of LOLS chilldown L-01H 45M: 15 minute hold T-01H 30M: Start of propellant loading T-00H 25M: Start of engine low flow chilldown T-00H 10M: Start of engine medium flow chilldown T-00H 03M 30S: Initiate autosequencer transition (terminal count) T-00H 03M 00S: Autosequencer control T-00H 00M 00.5S: Initiation launch ordnance train T-00H 00M 00S: Launch (1700 EDT) T+1.5 seconds: Engine health checks complete T+2 seconds: Liftoff L+6 seconds: TEL clear 20 A-ONE Launch Ascent Profile and Mark Events Launch Site Wallops Flight Facility Va. Longitude -75.5o E Latitude 37.4o N Altitude 0.028 km Azimuth 107.8o No. Event Time(s) Altitude Latitude Longitude Velocity (Km) (Deg) (Deg) (m/s) 1 Stage 1 Ignition 0.0 0.0 37.8 -75.5 0 2 Lift Off 2.0 0.0 37.8 -75.5 0 3 MECO 230.0 107 36.6 -73.1 4402 4 Stage 1 Separation 235.0 113 36.5 -72.9 4403 5 Fairing Separation 319.0 184 34.7 -69.8 4251 6 Interstage Separation 324.0 186.8 34.6 -69.6 4244 7 Stage 2 Ignition 328.0 189 34.5 -69.5 4240 8 Stage 2 Burn-out / 483.0 256 29.4 -62.9 7468 Orbit Insertion 9 Payload Separation 603.0 255 23.5 -57.1 7475 21 JFS-4/3/13 © 2013 Orbital Sciences Corporation. All Rights Reserved. A-ONE Mission Ground Track Payload Separation Stage 2 Burnout Fairing Separation/ Interstage Separation/ Stage 2 Ignition MECO/Stage 1 Separation JFS-3/25/13 22 © 2013 Orbital Sciences Corporation. All Rights Reserved. A-ONE Mission Telemetry Coverage L-0 sec L+231 sec L+236 sec L+319 sec L+328 sec L+483 sec L+603 sec L+606 sec L+1123 sec Stage 1 Stage 1 Fairing Stage 2 Stage 2 Payload Begin C/CAM Ignition MECO Separation Separation Ignition Burnout Separation EOM TELEMETRY (RocketCam) (Stage 2 Avionics) (P/L Instrumentation) (LV Instrumentation) (Stage 1 Avionics) Wallops Coquina Bermuda Antigua FLIGHT TERMINATION Wallops (FTS Receiver) Coquina Bermuda L+440 sec No FTS Req’t RADAR Wallops (Transponder) Coquina Bermuda JFS-3/25/13 23 © 2013 Orbital Sciences Corporation. All Rights Reserved. Cygnus Status COTS Mission Pressurized Cargo Element Loaded with Cargo at Wallop Flight Facility Payload Integration Center Additional Cargo To Be Loaded Prior to Launch COTS Service Module, Along with Two Others, Assembled in Orbital Dulles Factory 24 © 2013 Orbital Sciences Corporation. All Rights Reserved. Summary Orbital is Moving Into Antares Test Launch with High Confidence Successful Test Launch Will Validate Antares System Performance Successful Test Launch Will be Followed By COTS Demonstration Launch After Data Review and Vehicle Preparations JFS-4/3/13 © 2013 Orbital Sciences Corporation. All Rights Reserved. 25 Orbital Proprietary 26 .
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