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Atlas V GPS IIF-8 Mission Brochure

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Atlas V GPS IIF-8 Mission Brochure ATLAS V GPS IIF-8 MISSION A United Launch Alliance Atlas V 401 vehicle will deliver the GPS IIF-8 satellite to semi-synchronous circular orbit. Liftoff will occur from Space Launch Complex 41 at Cape Canaveral Air Force Station, FL. The Navstar GPS is a constellation of satellites that provides navigation data to military and civilian users worldwide. The system is operated The ULA team is proud to be the launch provider for the U.S. Air Force and controlled by the 50th Space Wing, located at Schriever Air Force (USAF) Global Positioning System (GPS) Directorate by delivering Base, CO. replenishment satellites aboard Atlas V and Delta IV launch vehicles. GPS IIF-8 is one of the next generation GPS satellites, incorporating GPS utilizes 24 satellites, in six different planes, with a minimum of various improvements to provide greater accuracy, increased signals, four satellites per plane, positioned in orbit approximately 11,000 and enhanced performance for users. miles above the Earth’s surface. The satellites continuously transmit digital radio signals pertaining to the exact time (using atomic clocks) and exact location of the satellites. The GPS IIF series have a design life of 12 The ULA team is focused on attaining Perfect Product Delivery for the years. With the proper equipment, users can receive these signals to calculate time, location, and velocity. The signals are so accurate that time can be GPS IIF-8 mission, which includes a relentless focus on mission suc- measured to within a millionth of a second, velocity within a fraction of a mile per hour, and location to within feet. Receivers have been developed for cess (the perfect product) and also excellence and continuous improve- use in aircraft, ships, land vehicles, and to hand carry. ment in meeting all of the needs of our customers (the perfect delivery). As a result of increased civil and commercial use as well as experience in military operations, the USAF has added the following capabilities and tech- My thanks to the entire ULA team, including our suppliers, as well as our nologies to the GPS IIF series to sustain the space and control segments while improving mission performance: mission partners — the USAF and the Aerospace Corporation — for their hard work and commitment to mission success. – Two-times greater predicted signal accuracy than heritage satellites. – New L5 signals for more robust civil and commercial aviation. Go Atlas, Go Centaur, Go GPS! – An on-orbit, reprogrammable processor, receiving software uploads for improved system operation. – Military signal “M-code” and variable power for better resistance to jamming hostile environments, meeting the needs of emerging doctrines of navigation warfare. Jim Sponnick Vice President, Atlas and Delta Programs Payload Fairing (PLF) The GPS IIF-8 spacecraft is encapsulated in the 4-m (14-ft) diameter large payload fairing (LPF). The LPF 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 189 ft. Centaur The Centaur second stage is 10 ft in diameter and 41.5 ft in length. Its propellant tanks are MISSION OVERVIEW constructed of pressure-stabilized, corrosion resistant stainless steel. Centaur is a cryogenic vehicle, fueled with liquid hydrogen and liquid oxygen. It uses a single RL10A-4-2 engine producing 22,300 lb of thrust. The cryogenic tanks are insulated with a combination of helium-purged insu- lation blankets, radiation shields, and spray-on foam insulation (SOFI). The Centaur forward adapter PMS 280C PMS 279C PMS 123C Black With more than a century of combined heritage, United Launch Alliance is – 26th Atlas V 401 Configuration Launch (CFA) provides the structural mountings for the fault-tolerant avionics system and the structural and the nation’s most experienced and reliable launch service provider. ULA th electrical interfaces with the spacecraft. has successfully delivered more than 85 satellites to orbit that provide – 50 Atlas V Launch critical capabilities for troops in the field, aid meteorologists in tracking – 8th GPS Block IIF Satellite Booster severe weather, enable personal device-based GPS navigation and unlock The Atlas V booster is 12.5 ft in diameter and 106.5 ft in length. The booster’s tanks are structur- the mysteries of our solar system. – 55th Operational GPS Satellite to Launch on a ULA Rocket ally 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. The Atlas V booster is controlled by the Join the conversation: Centaur avionics system, which provides guidance, flight control, and vehicle sequencing functions during the booster and Centaur phases of flight. Bringing Rocket Science Down to Earth. ULALaunch.com Copyright © 2014 United Launch Alliance, LLC. All Rights Reserved. PMS 280C PMS 279C PMS 123C Black ATLAS V PRODUCTION AND LAUNCH MISSION PROFILE AND GROUND TRACE 1 DeDenver, Soto, CO CA • RS-68 Engine Fabrication at Aerojet Rocketdyne 1 De– ULA Soto, Headquarters CA & Design 7 8 2 2 Brigham• CenterRS-68 EngineeringEngine City ,F abricationUT at Aerojet Rocketdyne 6 1 De•Harlingen, Solid Soto, Rocket TXCA Motor Fabrication at Alliant Technologies 2 3 21 DeBrigham Soto, CACity, UT 5 13 Denver•De– SolidRS-68Payload Soto, Rocket ,Engine Fairing,CO CA Motor F Payloadabrication Fabrication Fairing at Aerojet at Alliant Rocketdyne Technologies 1 3 •De RS-68 Soto, Engine CA Fabrication at Aerojet Rocketdyne 21 Brigham• Adapter, Booster City, UTAdapter & Centaur 2 23 Brigham•Denver RS-68ULA Headquarters ,Engine CO City ,F abricationUT & Design at AerojetCenter EngineeringRocketdyne Time Time 1 2 4 2 •Brigham AdapterSolid Rocket Fabrication City Motor, UT Fabrication at Alliant Technologies Event 3 4 24 BrighamDecatur• SolidULA HeadquartersRocket, ALCity Motor, UT & F abricationDesign Center at Alliant Engineering Technologies (seconds) (hr:min:sec) 2 3 3 • Decatur, Solid Rocket AL Motor Fabrication at Alliant Technologies 4 1 3 4 Decatur•Denver SolidPayload Rocket, ,FCO ALairing/Adapter Motor Fabrication Fabrication at Alliant Technologies 1 RD-180 Engine Ignition -2.7 -00:00:02.7 1 3 Denver– Booster, FabricationCO & Final Assembly, 1 3 5 • PBoosterULAayload Headquarters Fabricationairing/Adapter & Design Fabrication Center Engineering 4 3 •Denver ULA Headquarters, CO & Design Center Engineering Liftoff (Thrust to Weight > 1) 1.1 00:00:01.1 1 4 5 • CentaurBoosterSecond TankStageFabrication Fabrication Fabrication & Centaur 4 •Decatur FinalULA HeadquartersAssembly, AL & Design Center Engineering 4 4 •Decatur PSecondayload ,StageF ALairing/Adapter Fabrication Fabrication Begin Pitch/Yaw Maneuver 17.2 00:00:17.2 5 • Payload Fairing/Adapter Fabrication 4 •DecaturWWest BoosterPestayload Palm Palm ,F ALabricationairing/AdapterBeach, Beach, FL FL Fabrication 5 • BoosterRL10 Engine Fabrication Fabrication at Aerojet Rocketdyne Mach 1 78.5 00:01:18.5 5 5 •W– SecondBoosterPRL10estayload P Enginealm StageFabricationairing/Adapter Beach, Fabrication Fabrication FL F atabrication Aerojet 5 • RocketdyneSecondBoosterRL10 Engine StageFabrication F Fabricationabrication at Aerojet Rocketdyne Maximum Dynamic Pressure 90.3 00:01:30.3 5 • Second Stage Fabrication 5 WKhimki,est P Russiaalm Beach, FL 2 5 •W RL10est P Enginealm Beach, Fabrication FL at Aerojet Rocketdyne Atlas Booster Engine Cutoff (BECO) 243.8 00:04:03.8 •– RL10RD-180 Engine Engine Fabrication Fabrication at atAerojet NPO Rocketdyne 3 5 •W RL10est P Enginealm Beach, Fabrication FL at Aerojet Rocketdyne Atlas Booster/Centaur Separation 249.8 00:04:09.8 • EnergomashRL10 Engine Fabrication at Aerojet Rocketdyne 3 Centaur Main Engine Start (MES-1) 259.8 00:04:19.8 4 Payload Fairing Jettison 267.8 00:04:27.8 1 Atlas Spaceflight Operations Center (ASOC) | Launch Control Center and Mission Director’s Center 5 Centaur First Main Engine Cutoff (MECO-1) 1,029.4 00:17:09.4 2 Spacecraft Processing Facility | Spacecraft processing, 1 Vertical Integration Facility (VIF) 6 Centaur Second Main Engine Start (MES-2) 11,882.1 03:18:02.1 testing and encapsulation (See inset) 2 7 Centaur Second Main Engine Cutoff (MECO-2) 11,971.8 03:19:31.8 3 Vertical Integration Facility | Launch vehicle Integration 2 Bridge Crane Hammerhead 3 8 GPS IIF-8 Separation 12,257.5 03:24:17.5 and testing, spacecraft mate and integrated operations 3 Bridge Crane 4 Launch Vehicle Perigee Altitude: 11,047 nmi | Apogee Altitude: 141,047 nmi | Inclination: 55.0 deg | Flight Azimuth: 45.8 deg Interstage 2 Adapter Booster 5 Mobile Launch Platform (MLP) Longitude (deg) 6 Centaur LO Storage 2 4 7 High Pressure Gas Storage 5 80 1 Centaur 8 Booster LO Storage 2 5 60 9 Pad Equipment Building (PEB) BOSS 5 LION 10 Pad ECS Shelter 40 ER 3 20 (deg) Spacecraft Guam 4-m Payload 0 Fairing Halves TDRS 046 TDRS 041 Diego Garcia Payload 1 -20 Geodetic Latitude Transporter -40 6 7 8 -60 4 1 Telemetry Ground Station Launch Vehicle /Spacecraft Ground Trace 2 10 TDRS Asset Geostationary Orbital Position -80 3 6 -135 -90 -45 0 45 90 135 Mobile 7 8 Launch Space Launch Complex 41 Platform 9 All Values Approximate.
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