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Delta IV WGS-8 Mission Overview

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Delta IV WGS-8 Mission Overview DELTA IV WGS-8 MISSION DELTA IV MEDIUM+ (5,4) A United Launch Alliance (ULA) Delta IV Medium+ (5,4) will The Delta IV family of launch vehicles combines design simplicity, deliver the eighth Wideband Global SATCOM (WGS) satellite to manufacturing efficiency, and streamlined mission and vehicle integration supersynchronous transfer orbit. Liftoff will occur from Space Launch to meet customer launch requirements. The Delta IV Medium+ (5,4) Complex-37 at Cape Canaveral Air Force Station (CCAFS), FL. configuration has launched five WGS satellites. First Launch: Dec. 5, 2009 WGS-8, the second Block II follow-on satellite, supports commu- Launches to date: 5 nications links in the X-band and Ka-band spectra. While Block I and II satellites can instantaneously filter and downlink up to 4.410 Image courtesy of The Boeing Company Performance to GTO: 6,890 kg (15,109 lb) GHz, WGS-8 can filter and downlink up to 8.088 GHz of bandwidth. Performance to LEO-Reference: 13,370 kg (30,250 lb) Depending on the mix of ground terminals, data rates, and modulation and coding schemes employed, a single WGS satellite can support data transmis- sion rates over 6 Gbps, and WGS-8 with its advanced digital channelizer may support over 11 Gbps. The current fleet is providing more than 16 Gbps globally, and the most heavily loaded WGS vehicle is now providing over 4 Gbps locally. 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-8 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 – 34th Delta IV Launch the nation’s most experienced and reliable launch service provider. ULA Booster th has successfully delivered more than 110 satellites to orbit that provide – 114 ULA Launch 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 in- sulation blankets. The booster is controlled by the DCSS avionics system, which provides guidance, flight control. Join the conversation: Solid Rocket Motors (SRM) Four SRMs generate the additional thrust required for liftoff and attain a combined maximum thrust of 1,124,000 lbs in flight. The SRMs are 5 ft in diameter and 53 ft long and constructed of a ULALaunch.com graphite-epoxy composite. The SRMs are connected to the booster by two ball-and-socket joints and structural thrusters. Copyright © 2016 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 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 2 3 2 Brigham• Solid Rocket City Motor, UT Fabrication at Alliant Technologies Time Time 3 3 Denver• atULASolid Alliant HeadquartersRocket, COTechnologies Motor & F abricationDesign Center at Alliant Engineering Technologies 5 Event (seconds) (hr:min:sec) 1 3 4 3 Denver• Solid Rocket, CO Motor Fabrication at Alliant Technologies 1 3 3 Denver•Denver, ULA Headquarters CO, CO & Design Center Engineering RS-68A Engine Ignition -5.0 -0:00:05.0 1 4 •Decatur , AL 1 4 3 •Denver– ULA Headquarters, CO & Design Center Engineering 1 4 4 Decatur• PULAayload Headquarters ,F ALairing/Adapter & Design Fabrication Center Engineering Liftoff (Thrust to Weight > 1) 0.0 0:00:00.0 4 Decatur• CenterULA Headquarters Engineering, AL & Design Center Engineering 4 5 4 Decatur• PBoosterayload ,F ALabricationairing/Adapter Fabrication Begin Pitch/Yaw/Roll Maneuver 7.0 0:00:07.0 4 •DecaturDecatur, PBoosterSecondayload AL ,StageF ALabricationairing/Adapter Fabrication Fabrication 5 Maximum Dynamic Pressure 46.2 0:00:46.2 5 •– BoosterSecondPBooster,ayload StageFPayloadabricationairing/Adapter Fabrication Fairing andFabrication 5 5 •W SecondBoosterest Palm StageFabrication Beach, FabricationFabrication FL 2 SRM 3,4 Burnout 91.6 0:01:31.6 • SecondRL10 Engine Stage F Fabricationabrication at Aerojet Rocketdyne 5 WWestest Palm Palm Beach, Beach, FL FL SRM 1,2 Burnout 93.1 0:01:33.1 5 •W RL10est P Enginealm Beach, Fabrication FL at Aerojet Rocketdyne W– RL10est P Enginealm Beach, Fabrication FL at Aerojet 5 •W RL10est P Enginealm Beach, Fabrication FL at Aerojet Rocketdyne 4 SRM Jettison 1 100.0 0:01:40.0 • RocketdyneRL10 Engine Fabrication at Aerojet Rocketdyne SRM Jettison 2 102.4 0:01:42.4 3 Payload Fairing Jettison 194.4 0:03:14.4 4 Booster Engie Cutoff (BECO) 236.0 0:03:56.0 5 First-Stage Separation 242.0 0:04:02.0 1 Delta Operations Center (DOC) | Launch Control Center 6 Main Engine Start (MES-1) 255.0 0:04:15.0 and Mission Director’s Center 7 Main Engine Cutoff (MECO-1) 1,191.8 0:19:51.8 2 Horizontal Integration Facility | Receiving, inspection 1 Mobile Service Tower (MST) and integration 8 Second Main Engine Start (MES-2) 1,765.6 0:29:26.6 2 3 Launch Vehicle 9 3 Receipt Inspection Shop | Receiving, inspection and Second Main Engine Cutoff (MECO-2) 1,953.6 0:32:33.6 3 Launch Table processing 10 WGS-8 Separation 2,503.6 0:41:43.6 4 Fixed Umbilical Tower (FUT) 4 Spacecraft Processing Facility | Spacecraft processing, Perigee Altitude: 235 nmi | Apogee Altitude: 23,962 nmi | Inclination: 27 deg | Flight Azimuth: 93.46 deg testing and encapsulation 5 Lightning Protection Towers 1 Delta Operations Center (DOC) 5 Mobile Service Tower | Launch vehicle integration and 6 LH2 Storage Tank Longitude (deg) Launch Control Center testing, spacecraft mate and integrated operations Mission Director’s Center 7 Second Stage Nozzle Extension Installation LO2 Storage Tank 1 80 Spacecraft Control Room Communication Center Solid Rocket Motors 60 2 Horizontal Integration Facility 1 Receiving & Inspection 5 Vehicle Integration 2 5-m DCSS 40 3 Receipt Inspection Shop Booster Receiving & Inspection TEL-4 Staging Final Processing 20 4 (deg) 4 Spacecraft Processing 3 Facility TDRS-E 2 0 7 Spacecraft Processing, 6 Diego Testing & Encapsulation 2 8 Garcia 5 Mobile 7 -20 Geodetic Latitude Service Tower 9 Launch Vehicle Integration & Testing, Spacecraft Mate, 5-m Fairing 3 10 Integrated Operations Halves -40 5-m Payload Adapter Fittings Umbilical Tower -60 Payload 1 Telemetry Ground Station Launch Transporter Spacecraft Launch Vehicle /Spacecraft Groundtrack Table 4 5 TDRS Asset Geostationary Orbital Position -80 -135 -90 -45045 90 135 Space Launch Complex-37 All Values Approximate.
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