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Delta IV WGS-9 Mission Overview

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Delta IV WGS-9 Mission Overview DELTA IV WGS-9 MISSION DELTA IV MEDIUM+ (5,4) A United Launch Alliance (ULA) Delta IV Medium+ (5,4) will deliver The Delta IV family of launch vehicles combines design simplicity, the ninth Wideband Global SATCOM (WGS) satellite to supersynchro- manufacturing efficiency, and streamlined mission and vehicle integration nous transfer orbit. Liftoff will occur from Space Launch Complex-37 to meet customer launch requirements. The Delta IV Medium+ (5,4) at Cape Canaveral Air Force Station (CCAFS), FL. configuration has launched six WGS satellites. First Launch: Dec. 5, 2009 WGS-9, the third Block II follow-on satellite, supports communica- Launches to date: 6 tions links in the X-band and Ka-band spectra. While Block I and II satellites can instantaneously filter and downlink up to 4.410 GHz, Image courtesy of The Boeing Company Performance to GTO: 6,890 kg (15,109 lb) WGS-9 can filter and downlink up to 8.088 GHz of bandwidth. De- Performance to LEO-Reference: 13,370 kg (30,250 lb) pending on the mix of ground terminals, data rates and modulation and coding schemes employed, a single WGS satellite can support data transmission rates over 6 Gbps, and WGS-9 with its advanced digital channelizer may support over 11 Gbps. WGS has 19 independent coverage areas, 18 of which can be positioned throughout its field-of-view. This includes eight steerable/shapeable X-band beams formed by separate transmit/receive phased arrays; 10 Ka-band beams served by independently steerable diplexed antennas; and one transmit/ receive X-band Earth-coverage beam. WGS can tailor coverage areas and connect X-band and Ka-band users anywhere within its field-of-view. The X-band phased array antenna enables anti-jam functionality without sacrificing performance. Five globally-located Army Wideband SATCOM Operations Centers provide 24/7 payload monitoring and command and control of the WGS constella- tion. In coordination with the WGS-9 launch, the US Army has modernized the Global SATCOM Configuration and Control Element to a new service-ori- ented virtualized software system residing on a new ground hardware platform. Each Global Satellite Configuration and Control Element has the capability to control up to ten WGS satellites at a time. Spacecraft platform control and anomaly resolution is accomplished by the 3rd Space Operations Squadron at Schriever Air Force Base in Colorado Springs, CO. Payload Fairing (PLF) The PLF is a composite bisector (two-piece shell), 5-meter diameter fairing. The PLF encapsulates the spacecraft to protect it from the launch environment on ascent. The vehicle’s height, with the 47-ft tall PLF, is approximately 217 ft. Delta Cryogenic Second Stage (DCSS) The DCSS propellant tanks are structurally rigid and constructed of formed aluminum plate, spun-formed aluminum domes and aluminum ring forgings. It is a cryogenic liquid hydrogen/liquid MISSION OVERVIEW oxygen-fueled vehicle, powered by a single RL10B-2 engine that produces 24,750 lbf of thrust. The DCSS cryogenic tanks are insulated with a spray-on insulation and helium-purged insulation blankets. An equipment shelf attached to the aft dome of the DCSS liquid oxygen tank provides the structural mountings for vehicle electronics. With more than a century of combined heritage, United Launch Alliance is – 35th Delta IV Launch the nation’s most experienced and reliable launch service provider. ULA Booster – 118th ULA Launch has successfully delivered more than 115 satellites to orbit that provide The Delta IV common booster core (CBC) tanks are structurally rigid and constructed of isogrid alu- critical capabilities for troops in the field, aid meteorologists in tracking minum barrels, spun-formed aluminum domes and machined aluminum tank skirts. Delta IV booster severe weather, enable personal device-based GPS navigation and unlock propulsion is provided by the throttleable RS-68A engine system which burns cryogenic liquid the mysteries of our solar system. hydrogen and liquid oxygen and delivers 705,250 lbf of thrust at sea level. The booster’s cryogenic tanks are insulated with a combination of spray-on and bond-on insulation and helium-purged insulation blankets. The booster is controlled by the DCSS avionics system, which provides guid- ance, flight control. Four solid rocket motors (SRM) generate the additional power required at liftoff, Join the conversation: with each SRM providing 281,000 lbf of thrust. The SRMs are 5 ft in diameter, 53 ft long and are constructed of a graphite-epoxy composite. ULALaunch.com Copyright © 2017 United Launch Alliance, LLC. All Rights Reserved. DELTA IV PRODUCTION AND LAUNCH MISSION PROFILE AND GROUND TRACE 1 De Soto,Soto, CA CA 1 De•– RS-68RS-68A Soto, Engine Engine CA F abricationFabrication at at Aerojet Rocketdyne 7 8 9 10 21 De• AerojetRS-68 Soto, EngineRocketdyne CA Fabrication at Aerojet Rocketdyne 2 1 •Brigham RS-68 Engine City ,F abricationUT at Aerojet Rocketdyne 6 21 Brigham•De SolidRS-68 Soto, Rocket EngineCity, CACity UTMotor ,F abricationUT Fabrication at Aerojet at Alliant Rocketdyne Technologies 11 2 3 2 Brigham• RS-68 Engine City ,F abricationUT at Aerojet Rocketdyne 2 23 DenverBrigham•– Solid Rocket, CO City Motor, UT FabricationFabrication at Alliant Technologies 1 3 2 Brigham• Solid Rocket City Motor, UT Fabrication at Alliant Technologies 2 3 3 Denver• atULASolid Orbital HeadquartersRocket, CO ATK Motor & F abricationDesign Center at Alliant Engineering Technologies 5 1 3 4 3 Denver• Solid Rocket, CO Motor Fabrication at Alliant Technologies 12 1 3 3 Denver•Denver, ULA Headquarters CO, CO & Design Center Engineering Time 1 4 •Decatur , AL Event 4 3 •Denver– ULA Headquarters, CO & Design Center Engineering (hr:min:sec) 1 4 4 Decatur• PULAayload Headquarters ,F ALairing/Adapter & Design Fabrication Center Engineering 4 • CenterULA Headquarters Engineering & Design Center Engineering 1 RS-68A Engine Ignition -0:00:05.0 4 5 4 Decatur• PBoosterayload ,F ALabricationairing/Adapter Fabrication 5 4 •DecaturDecatur, PBoosterSecondayload AL ,StageF ALabricationairing/Adapter Fabrication Fabrication Liftoff (Thrust to Weight > 1) 0:00:00.0 5 •– BoosterSecondPULAayload Booster, StageFabricationairing/Adapter Payload Fabrication Fairing Fabrication and Begin Pitch/Yaw/Roll Maneuver 0:00:07.0 5 W• Secondest Palm Stage Beach, Fabrication FL 5 • SecondBooster StageFabrication FabricationFabrication Maximum Dynamic Pressure 0:00:46.1 5 W• SecondRL10est P Enginealm Stage Beach, F Fabricationabrication FL at Aerojet Rocketdyne 5 West Palm Beach, FL 5 W• RL10est P Enginealm Beach, Fabrication FL at Aerojet Rocketdyne 2 SRM 3,4 Burnout 0:01:32.8 •– RL10 Engine FabricationFabrication at Aerojet Rocketdyne 5 •W RL10est P Enginealm Beach, Fabrication FL at Aerojet Rocketdyne 4 SRM 1,2 Burnout 0:01:35.1 • RocketdyneRL10 Engine Fabrication at Aerojet Rocketdyne SRM Jettison 1 0:01:40.1 SRM Jettison 2 0:01:42.4 3 Payload Fairing Jettison 0:03:14.6 13 4 Booster Engie Cutoff (BECO) 0:03:56.5 1 Delta Operations Center (DOC) | Launch Control Center 7 and Mission Director’s Center 5 First Stage Separation 0:04:03.1 Park Orbit Re-entry Orbit 2 Horizontal Integration Facility | Receiving, inspection 1 Mobile Service Tower (MST) 6 Main Engine Start (MES-1) 0:04:16.1 8 SV Orbit and integration 3 2 Launch Vehicle 7 Main Engine Cutoff (MECO-1) 0:19:53.6 9 3 Receipt Inspection Shop | Receiving, inspection and 8 Second Main Engine Start (MES-2) 0:29:26.6 processing 3 Launch Table 9 Second Main Engine Cutoff (MECO-2) 0:32:35.3 10 4 Spacecraft Processing Facility | Spacecraft processing, 4 Fixed Umbilical Tower (FUT) 10 WGS-9 Separation 0:41:45.6 11 12 testing and encapsulation 5 Lightning Protection Towers 11 Third Main Engine Start (MES-3) 1:11:44.6 1 Delta Operations Center (DOC) 5 Mobile Service Tower | Launch vehicle integration and 6 LH2 Storage Tank WGS-9 Orbit at Separation: Launch Control Center testing, spacecraft mate and integrated operations 12 Third Main Engine Cutoff (MECO-3) 1:11:54.8 Perigee: 235 nmi | Apogee: 23,959 nmi Mission Director’s Center 7 Second Stage Nozzle Extension Installation LO2 Storage Tank 1 Inclination: 27 deg | Flight Azimuth: 93.46 deg Spacecraft Control Room 13 Ocean Impact 12:12:09.6 Communication Center Solid Rocket Motors 2 Horizontal Integration Facility 1 Longitude (deg) Receiving & Inspection 5 Vehicle Integration 2 80 5-m DCSS 3 Receipt Inspection Shop Booster Receiving & Inspection 60 Staging Final Processing 4 4 Spacecraft Processing 3 40 Facility TEL-4 Spacecraft Processing, 6 2 Testing & Encapsulation 2 20 (deg) 5 Mobile 7 TDRS-E 13 Service Tower 0 7 Launch Vehicle Integration Diego & Testing, Spacecraft Mate, 5-m Fairing 3 Garcia Integrated Operations Halves 8 5-m Payload -20 Geodetic Latitude Adapter 9 Fittings Umbilical 10 12 Tower 11 Payload 1 -40 Launch Transporter Spacecraft Table 4 5 -60 Telemetry Ground Station Launch Vehicle /Spacecraft Groundtrack TDRS Asset Geostationary Orbital Position -80 Space Launch Complex-37 -135 -90 -45045 90 135 All Values Approximate.
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