ATLAS V ECHOSTAR XIX MISSION ATLAS V 431 An Atlas V 431 rocket will deliver EchoStar’s XIX satellite to geosyn- The Atlas V 431 configuration rocket, with three solid rocket boosters, chronous transfer orbit (GTO). The United Launch Alliance (ULA) provides the optimum performance to precisely deliver a range of Atlas V rocket is provided to Lockheed Martin Commercial Launch mission types. In service for more than ten years, the Atlas V 431 Services. Liftoff will occur from Space Launch Complex-41 at Cape configuration rocket has launched two commercial communications Canaveral Air Force Station, Florida. satellites where they provide global communications from geostationary orbit. EchoStar XIX will be the world’s highest capacity broadband satellite First Launch: Mar. 11, 2005 ® in orbit, dramatically increasing capacity for HughesNet high-speed Launches to date: 2 satellite Internet service to homes and businesses in North America. This large, multi-spot beam Ka-band satellite, based on the powerful Performance to GTO: 7,700 kg (16,970 lb) SSL 1300 platform, will be stationed at 97.1 degrees West longitude. Performance to LEO-Reference: 15,260 kg (33,660 lb) Building from their experience on the highly successful EchoStar XVII broadband satellite, SSL and Hughes collaboratively engineered the specific design details of this payload for optimum performance. Satellite Image Courtesy of EchoStar Payload Fairing (PLF) The EchoStar XIX satellite is encapsulated in the 4-m (14-ft) diameter extra extend- ed 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. 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 hydrogen/liquid oxygen- (cryogenic-) fueled vehicle. It uses a single RL10C-1 engine producing 22,900 lbf of thrust. The cryogenic tanks are insulated with a combination of helium-purged insulation blankets, radiation shields, and spray-on foam insulation (SOFI). The Centaur forward adapter (CFA) provides the structural mountings for the fault-tolerant avionics system and the structural and electrical interfaces with the spacecraft. Booster MISSION OVERVIEW 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 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 Propellant-1 or highly purified kerosene) and liquid oxygen, and delivers 860,200 lb of thrust at sea level. Three solid rocket boosters (SRB) With more than a century of combined heritage, United Launch Alliance – 68th Atlas V Launch generate the additional power required at liftoff, with each SRB providing 348,500 is the nation’s most experienced and reliable launch service provider. – 115th ULA Launch lb of thrust. The Atlas V booster is controlled by the Centaur avionics system, which ULA has successfully delivered more than 110 satellites to orbit that provides guidance, flight control, and vehicle sequencing functions during the boost- provide critical capabilities for troops in the field, aid meteorologists in er and Centaur phases of flight. tracking severe weather, enable personal device-based GPS navigation and unlock the mysteries of our solar system. Join the conversation: ULALaunch.com Copyright © 2016 United Launch Alliance, LLC. All Rights Reserved. ATLAS V PRODUCTION AND LAUNCH MISSION PROFILE AND GROUND TRACE 1 DeSacramento, Soto, CA CA 1 De•– RS-68Solid Soto, Rocket Engine CA Booster Fabrication Fabrication at Aerojet at Rocketdyne 1 De Soto, CA1. 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Harlingen, & Design Center TX Engineering 4 3 •Denver– ULASolidPayload HeadquartersRocket, Fairing,CO Motor Payload & F abricationDesign Fairing Center atAdapter, Alliant Engineering BoosterTechnologies 1 3 4 4 Decatur• Payload ,F ALairing/Adapter– Payload F abricationFairing, Payload Fairing Adapter, Booster Adapter & Centaur Time Time 43 Denver• AdapterULA Headquarters, &CO Centaur Adapter& Design Fabrication Center Engineering Event 1 4 5 4 Decatur• PBoosterayload ,F ALabricationairing/Adapter Fabrication (seconds) (hr:min:sec) • Payload Fairing/AdapterAdapter FFabricationabrication 4 •DecaturDecatur, BoosterPSecondULAayload Headquarters AL ,StageF ALabricationairing/Adapter Fabrication & Design Fabrication Center Engineering 1 RD-180 Engine Ignition -2.7 -00:00:02.7 4 5 • Booster Fabrication4. Decatur, AL 5 4 Decatur•– SecondBoosterPayload ,StageFabricationF ALabricationairing/Adapter Fabrication & Final Fabrication Assembly, Centaur Liftoff (Thrust to Weight > 1) 1.1 00:00:01.1 5 •W BoosterSecondest Palm StageFabrication –Beach, BoosterFabrication FL Fabrication & Final Assembly, Centaur Tank Fabrication & 5 5 • TankPSecondayload Fabrication StageFairing/Adapter F abrication& Centaur Fabrication Final Assembly Begin Pitch/Yaw Maneuver 5.5 00:00:05.5 5 • SecondRL10 Engine StageCe F Fabricationntaurabrication F inalat Aerojet Assembly Rocketdyne 5 5 •WWest Boosterest Palm Palm F abricationBeach, Beach, FL FL 5 W• RL10est P Enginealm 5.Beach, F abricationWest PFLalm at Aerojet Beach, Rocketdyne FL Mach 1 45.4 00:00:45.4 •– RL10SecondRL10C-1 Engine Stage Engine F Fabricationabrication Fabrication at Aerojet at Aerojet Rocketdyne Rocket- 5 •W RL10est P Enginealm –Beach, FRL10abrication Engine FL at Aerojet Fabrication Rocketdyne at Aerojet Rocketdyne 3 Maximum Dynamic Pressure 57.7 00:00:57.7 dyne 65 W• RL10est P Enginealm 6.Beach, F abricationKhimk FLi, atRussia Aerojet Rocketdyne 2 SRB Jettison 125.1 00:02:05.1 Khimki, Russia • RL10 Engine– FRDabrication-180 Engineat Aerojet FRocketdyneabrication at Atlas Booster Engine Cutoff (BECO) 266.7 00:04:26.7 1 2 – RD-180 Engine Fabrication at NPO Energomash 3 Atlas Booster/Centaur Separation 272.7 00:04:32.7 4 Centaur Main Engine Start (MES-1) 282.7 00:04:42.7 4 1 Atlas Spaceflight Operations Center (ASOC) | Launch 5 Payload Fairing Jettison 290.7 00:04:50.7 6 Centaur First Main Engine Cutoff (MECO-1) 818.6 00:13:38.6 5 Control Center and Mission Director’s Center Centaur Second Main Engine Start (MES-2) 1,389.2 00:23:09.2 6 3 1 Vertical Integration Facility (VIF) 7 2 Delta Operations Center | ISA, Centaur, Boattail (See inset) Vertical Integration 8 Centaur Second Main Engine Cutoff (MECO-2) 1,737.6 00:28:57.6 2 Bridge Crane Hammerhead 2 9 EchoStar XIX Separation 1,923.7 00:32:03.7 3 Spacecraft Processing Facility | Spacecraft processing, 3 testing and encapsulation 3 Bridge Crane Perigee Altitude: 204 km | Apogee Altitude: 65,000 km | Inclination: 25.44 deg | Argument of Perigee: 180 deg 4 Vertical Integration Facility | Launch vehicle integration 4 Launch Vehicle and testing, spacecraft mate and integrated operations 2 5 Mobile Launch Platform (MLP) Longitude (deg) 6 Centaur LO Storage 2 4 7 High Pressure Gas Storage 5 80 4-m 1 Boattail Interstage 8 Booster LO2 Storage Adapter 60 LION Centaur 5 9 Pad Equipment Building (PEB) BOSS 10 Pad ECS Shelter 40 Booster TEL-4 2 20 4 (deg) HULA 6 Guam Spacecraft 4-m Payload 0 7 Delta Operations Center Fairing Halves REEF ISA, Centaur, Boattail TDRS 41 8 Vertical Integration 1 -20 9 Geodetic Latitude Payload Transporter 1 -40 3 -60 4 Telemetry Ground Station Launch Vehicle /Spacecraft Groundtrack 10 TDRS Asset Geostationary Orbital Position -80 4 Mobile 6 Launch Platform -135 -90 -45 0 45 90 135 Solid Rocket Boosters 7 8 Space Launch Complex-41 9 All Values Approximate.