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MISSION OVERVIEW Centaur the Centaur Second Stage Is 10 Ft in Diameter and 41.5 Ft in Length

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MISSION OVERVIEW Centaur the Centaur Second Stage Is 10 Ft in Diameter and 41.5 Ft in Length ATLAS V OA-7 MISSION ATLAS V 401 A United Launch Alliance (ULA) Atlas V 401 rocket will launch the The Atlas V 401 rocket has become the workhorse of the Atlas V fleet, Cygnus™ spacecraft on the initial leg of its cargo resupply mission delivering about half of all Atlas V missions to date. In its more than to the International Space Station (ISS). Liftoff will occur from Space 14 years of service, the 401 has launched a diverse set of missions Launch Complex-41 at Cape Canaveral Air Force Station, FL. including national security, science and exploration, commercial as well as International Space Station resupply. Orbital ATK developed the Cygnus advanced maneuvering spacecraft to perform ISS cargo delivery missions under the Commercial Resupply First Launch: Aug. 21, 2002 Service (CRS) contract with NASA. At a total weight of approximately Launches to date: 35 7,225 kg (15,928 lb), OA-7 will include approximately 3,380 kg Performance to GTO: 4,750 kg (10,470 lb) (7,452 lb) of internal cargo and an 83 kg (183 lb) external deployer Performance to LEO-Reference: 9,800 kg (21,600 lb) carrying CubeSats. Image Courtesy Orbital ATK Cygnus is a low-risk design incorporating elements drawn from Orbital ATK and its partners’ existing, flight-proven spacecraft technol- ogies. Cygnus consists of a common Service Module (SM) and a Pressurized Cargo Module (PCM). The SM is assembled and tested at Orbital ATK’s Dulles, VA, satellite manufacturing facility and incorporates systems from Orbital ATK’s flight-proven LEOStar™ and GEOStar™ satellite product lines. The PCM is based on the Multi-Purpose Logistics Module, developed and built by Thales Alenia Space of Italy. The OA-7 mission is the seventh Cygnus flight, and third Cygnus flight onboard an Atlas V rocket, following the extremely successful OA-4 and OA-6 launches in December 2015 and March 2016, respectively. The Cygnus spacecraft for the OA-7 mission will fly the Saffire-III experiment, developed and built by NASA’s Glenn Research Center, that tests properties of combustion in microgravity, as well as an external deployer carrying CubeSats that will be deployed after separation from the ISS. It is the fourth flight of Orbital ATK’s enhanced Cygnus featuring a larger PCM with increased cargo capacity and an optimized SM design including Orbital ATK’s lightweight UltraFlex™ solar arrays. Payload Fairing (PLF) The Cygnus spacecraft is encapsulated in the 4-m (14-ft) diameter extra extended payload fairing (XEPF). The XEPF is a bisector (two-piece shell) fairing consisting of aluminum skin/ stringer construction with vertical split-line longerons. The vehicle’s height with the PLF is approximately 194 ft. MISSION OVERVIEW Centaur The Centaur second stage is 10 ft in diameter and 41.5 ft in length. Its propellant tanks are constructed of pressure-stabilized, corrosion resistant stainless steel. Centaur is a liquid hy- rd drogen/liquid oxygen- (cryogenic-) fueled vehicle. It uses a single RL10C engine producing – 3 ULA Mission Supporting ISS Cargo Resupply 22,900 lbf of thrust. The cryogenic tanks are insulated with a combination of helium-purged With more than a century of combined heritage, United Launch Alliance – 71st Atlas V Launch insulation blankets, radiation shields, and spray-on foam insulation (SOFI). The Centaur is the nation’s most experienced and reliable launch service provider. forward adapter (CFA) provides the structural mountings for the fault-tolerant avionics system ULA has successfully delivered more than 115 satellites to orbit that and the structural and electrical interfaces with the spacecraft. provide critical capabilities for troops in the field, aid meteorologists in tracking severe weather, enable personal device-based GPS navigation Booster and unlock the mysteries of our solar system. The Atlas V booster is 12.5 ft in diameter and 106.5 ft in length. The booster’s tanks are structurally rigid and constructed of isogrid aluminum barrels, spun-formed aluminum Join the conversation: domes, and intertank skirts. Atlas booster propulsion is provided by the RD-180 engine system (a single engine with two thrust chambers). The RD-180 burns RP-1 (Rocket Pro- pellant-1 or highly purified kerosene) and liquid oxygen, and delivers 860,200 lb of thrust at sea level. The Atlas V booster is controlled by the Centaur avionics system, which provides ULALaunch.com guidance, flight control, and vehicle sequencing functions during the booster and Centaur phases of flight. Copyright © 2017 United Launch Alliance, LLC. All Rights Reserved. ATLAS V PRODUCTION AND LAUNCH MISSION PROFILE AND GROUND TRACE 1 DeDenver, Soto, CO CA 1 De•– RS-68ULA Soto, Headquarters Engine CA Fabrication & Design at Aerojet Rocketdyne 2 2 Brigham• CenterRS-68 EngineeringEngine City ,F abricationUT at Aerojet Rocketdyne 6 7 1 De•Harlingen, Solid Soto, Rocket TXCA Motor Fabrication at Alliant Technologies 8 2 3 21 DeBrigham Soto, CACity, UT 13 Denver•De– SolidRS-68Payload Soto, Rocket ,Engine Fairing,CO CA Motor F Boattail,abrication Fabrication Centaur at Aerojet at Alliant Rocketdyne Technologies 1 3 •De RS-68 Soto, Engine CA Fabrication at Aerojet Rocketdyne 5 21 Brigham• Forward Adapter, City, UT Aft Stub Adapter & 2 23 Brigham•Denver RS-68ULA Headquarters ,Engine CO City ,F abricationUT & Design at AerojetCenter EngineeringRocketdyne 1 2 4 2 •Brigham LaunchSolid Rocket Vehicle City Motor ,Adapter UT Fabrication Fabrication at Alliant Technologies 3 4 24 BrighamDecatur• SolidULA HeadquartersRocket, ALCity Motor, UT & F abricationDesign Center at Alliant Engineering Technologies 2 3 3 • Decatur, Solid Rocket AL Motor Fabrication at Alliant Technologies 1 3 4 Decatur•Denver SolidPayload Rocket, ,FCO ALairing/Adapter Motor Fabrication Fabrication at Alliant Technologies 1 3 Denver– Booster, FabricationCO & Final Assembly, 9 1 3 5 • PBoosterULAayload Headquarters Fabricationairing/Adapter & Design Fabrication Center Engineering 4 3 •Denver ULA Headquarters, CO & Design Center Engineering 1 4 5 • CentaurBoosterSecond TankStageFabrication Fabrication Fabrication & Centaur 4 4 •Decatur FinalULA HeadquartersAssembly, AL & Design Center Engineering 4 4 •Decatur PSecondayload ,StageF ALairing/Adapter Fabrication Fabrication Time 5 • Payload Fairing/Adapter Fabrication Event (hr:min:sec) 4 •DecaturWWest BoosterPestayload Palm Palm ,F ALabricationairing/AdapterBeach, Beach, FL FL Fabrication 5 • BoosterRL10 Engine Fabrication Fabrication at Aerojet Rocketdyne 5 5 •W– SecondBoosterPRL10Cestayload Palm EngineStageFabricationairing/Adapter Beach, FFabricationabrication FL Fabrication at Aerojet 1 RD-180 Engine Ignition -00:00:02.7 • Second Stage Fabrication 5 • RocketdyneSecondBoosterRL10 Engine StageFabrication F Fabricationabrication at Aerojet Rocketdyne Liftoff (Thrust to Weight > 1) 00:00:01.1 5 • Second Stage Fabrication 6 5 WKhimki,est P Russiaalm Beach, FL 5 5 •W RL10est P Enginealm Beach, Fabrication FL at Aerojet Rocketdyne Begin Pitch/Yaw Maneuver 00:00:18.4 •– RL10RD-180 Engine Engine Fabrication Fabrication at atAerojet NPO Rocketdyne 4 5 •W RL10est P Enginealm Beach, Fabrication FL at Aerojet Rocketdyne Mach 1 00:01:22.5 • EnergomashRL10 Engine Fabrication at Aerojet Rocketdyne 3 3 Maximum Dynamic Pressure 00:01:33.6 2 Atlas Booster Engine Cutoff (BECO) 00:04:15.6 1 Atlas Spaceflight Operations Center (ASOC) | Launch Atlas Booster/Centaur Separation 00:04:21.6 7 Control Center and Mission Director’s Center 3 Centaur Main Engine Start (MES-1) 00:04:31.6 8 1 Vertical Integration Facility (VIF) 2 Delta Operations Center | ISA, Centaur, Boattail (See inset) 4 Payload Fairing Jettison 00:04:39.6 Vertical Integration 2 Bridge Crane Hammerhead 2 5 Centaur Main Engine Cutoff (MECO-1) 00:18:12.0 Flight & Orbit Spacecraft processing, De-orbit 3 Spacecraft Processing Facility | 3 6 testing and encapsulation 3 Bridge Crane Cygnus Separation 00:21:01.1 9 7 Centaur Second Main Engine Start (MES-2) 00:48:30.4 4 Vertical Integration Facility | Launch vehicle integration 4 Launch Vehicle Cygnus Orbit at Separation: and testing, spacecraft mate and integrated operations 5 Mobile Launch Platform (MLP) 2 8 Centaur Second Main Engine Cutoff (MECO-2) 00:48:41.1 Perigee: 124.2 nmi | Apogee: 124.2 nmi Inclination: 51.6 deg | Flight Azimuth: 44.4 deg 6 Centaur LO Storage 9 Ocean Impact 01:07:06.6 2 4 5 7 High Pressure Gas Storage Longitude (deg) 4-m 1 Boattail Interstage 8 Booster LO Storage Adapter 2 5 80 Centaur 9 Pad Equipment Building (PEB) 10 Pad ECS Shelter 60 LION Booster BOSS 5 6 2 40 TEL-4 20 HULA (deg) Spacecraft Guam Delta Operations Center 4-m Payload TDRS 275 ISA, Centaur, Boattail Fairing Halves 0 Vertical Integration 1 REEF Payload TDRS 41 -20 7 Geodetic Latitude Transporter 8 -40 4 1 10 -60 Telemetry Ground Station 9 3 Launch Vehicle /Spacecraft Groundtrack 4 Mobile 6 TDRS Asset Geostationary Orbital Position Launch -80 Platform 7 8 -135 -90 -45 0 45 90 135 Space Launch Complex-41 9 All Values Approximate.
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