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GPS II F12

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JOSE ESPEJO VASQUEZ
JOSE ESPEJO VASQUEZ

The document summarizes an upcoming Atlas V 401 launch that will deliver a GPS IIF-12 satellite to semi-synchronous orbit. It will launch from Cape Canaveral Air Force Station, Florida. The GPS satellite is part of a constellation that provides navigation data to users worldwide. The Atlas V 401 rocket has successfully launched many missions, including previous GPS satellites.

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ATLAS V GPS IIF-12 MISSION ATLAS V 401 A United Launch Alliance Atlas V 401 launch vehicle will deliver the GPS IIF-12 satellite to semi-synchronous circular orbit. Liftoff will occur from Space Launch Complex-41 at Cape Canaveral Air Force Station, FL. The Navstar Global Positioning System (GPS) is a constellation of satellites that provides navigation data to military and civilian users worldwide. The system is operated and controlled by the 50th Space Wing, located at Schriever Air Force Base, CO. GPS utilizes 24 satellites, in six different planes, with a minimum of four satellites per plane, positioned in orbit approximately 11,000 nautical 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 years. With the proper equipment, users can receive these signals to calcu- late time, location, and velocity. The signals are so accurate that time can be 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 use in aircraft, ships, land vehicles, and to hand carry. 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- nologies to the GPS IIF series to sustain the space and control segments while improving mission performance: – Two times greater predicted signal accuracy than heritage satellites. – New L5 signals for more robust civil and commercial aviation. – 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. – 61st Atlas V Launch – 60th Operational GPS Satellite to Launch on a ULA Rocket – 12th GPS Block IIF Satellite MISSION OVERVIEW Copyright © 2016 United Launch Alliance, LLC. All Rights Reserved. The Atlas V 401 rocket has become the workhorse of the Atlas V fleet, delivering half of all Atlas V missions to date. In its nearly 14 years of service, the 401 has delivered 18 national security missions to orbit including five GPS satellites. The 401 rocket has also completed nine science and exploration flights, including two missions to Mars, a mission each to the sun and moon as well as a resupply mission to the International Space Station. First Launch: Aug. 21, 2002 Launches to date: 30 Performance to GTO: 4,750 kg (10,470 lb) Performance to LEO-Reference: 9,800 kg (21,600 lb) ing mission performance: stem operation. environments, Payload Fairing (PLF) The GPS IIF-12 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 con- structed of pressure-stabilized, corrosion resistant stainless steel. Centaur is a liquid hydrogen/liquid oxygen- (cryogenic-) fueled vehicle. It uses a single RL10C 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 The Atlas V booster is 12.5 ft in diameter and 106.5 ft in length. The booster’s tanks are structur- 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 Centaur avionics system, which provides guidance, flight control, and vehicle sequencing functions during the booster and Centaur phases of flight. With more than a century of combined heritage, United Launch Alliance is the nation’s most experienced and reliable launch service provider. ULA has successfully delivered more than 100 satellites to orbit that provide critical capabilities for troops in the field, aid meteorologists in tracking severe weather, enable personal device-based GPS navigation and unlock the mysteries of our solar system. Join the conversation: ULALaunch.com
2 3 1 Centaur Booster Interstage Adapter 4-m Payload Fairing Halves Spacecraft Mobile Launch Platform Payload Transporter Atlas Spaceflight Operations Center (ASOC) | Launch Control Center and Mission Director’s Center Spacecraft Processing Facility | Spacecraft processing, testing and encapsulation Vertical Integration Facility | Launch vehicle Integration and testing, spacecraft mate and integrated operations 1 3 2 4 4 6 7 5 9 2 5 3 8 1 10 Vertical Integration Facility (VIF) (See inset) Bridge Crane Hammerhead Bridge Crane Launch Vehicle Mobile Launch Platform (MLP) Centaur LO2 Storage High Pressure Gas Storage Booster LO2 Storage Pad Equipment Building (PEB) Pad ECS Shelter 1 4 5 3 2 6 7 8 9 10 Space Launch Complex 41 1 2 3 4 555 6 8 MISSION PROFILE AND GROUND TRACEATLAS V PRODUCTION AND LAUNCH Denver, CO – ULA Headquarters & Design Center Engineering Harlingen, TX – Payload Fairing, Boattail, Centaur Forward Adapter, Aft Stub Adapter, & Launch Vehicle Adapter Fabrication Decatur, AL – Booster Fabrication & Final Assembly, Centaur Tank Fabrication & Centaur Final Assembly West Palm Beach, FL – RL10C Engine Fabrication at Aerojet Rocketdyne Khimki, Russia – RD-180 Engine Fabrication at NPO Energomash 1 2 3 4 5 nter (ASOC) | LLaunch r er, & ion embly, taur rojet NPO Longitude (deg) GeodeticLatitude(deg) 80 60 40 20 0 -20 -80 -60 -40 -135 -90 -45 0 1359045 Telemetry Ground Station Launch Vehicle/Spacecraft Ground Trace TDRS Asset Geostationary Orbital Position ER Guam TDRS 041TDRS 046 BOSS LION Diego Garcia 5 6 7 8 All Values Approximate Time (hr:min:sec)Event 1 2 3 4 5 6 7 8 Time (seconds) RD-180 Engine Ignition -2.7 -00:00:02.7 Liftoff (Thrust to Weight > 1) 1.1 00:00:01.1 Begin Pitch/Yaw Maneuver 17.3 00:00:17.3 Mach 1 78.5 00:01:18.5 Maximum Dynamic Pressure 90.3 00:01:30.3 Atlas Booster Engine Cutoff (BECO) 243.9 00:04:03.9 Atlas Booster/Centaur Separation 249.9 00:04:09.9 Centaur Main Engine Start (MES-1) 259.9 00:04:19.9 Payload Fairing Jettison 267.9 00:04:27.9 Centaur First Main Engine Cutoff (MECO-1) 1,024.0 00:17:04.0 Centaur Second Main Engine Start (MES-2) 11,823.3 03:17:03.3 Centaur Second Main Engine Cutoff (MECO-2) 11,910.1 03:18:30.1 GPS IIF-12 Separation 12,196.1 03:23:16.1 Perigee Altitude: 11,047 nmi | Apogee Altitude: 11,047 nmi | Inclination: 55.0 deg | Flight Azimuth: 45.8 deg

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GPS II F12

  • 1. ATLAS V GPS IIF-12 MISSION ATLAS V 401 A United Launch Alliance Atlas V 401 launch vehicle will deliver the GPS IIF-12 satellite to semi-synchronous circular orbit. Liftoff will occur from Space Launch Complex-41 at Cape Canaveral Air Force Station, FL. The Navstar Global Positioning System (GPS) is a constellation of satellites that provides navigation data to military and civilian users worldwide. The system is operated and controlled by the 50th Space Wing, located at Schriever Air Force Base, CO. GPS utilizes 24 satellites, in six different planes, with a minimum of four satellites per plane, positioned in orbit approximately 11,000 nautical 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 years. With the proper equipment, users can receive these signals to calcu- late time, location, and velocity. The signals are so accurate that time can be 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 use in aircraft, ships, land vehicles, and to hand carry. 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- nologies to the GPS IIF series to sustain the space and control segments while improving mission performance: – Two times greater predicted signal accuracy than heritage satellites. – New L5 signals for more robust civil and commercial aviation. – 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. – 61st Atlas V Launch – 60th Operational GPS Satellite to Launch on a ULA Rocket – 12th GPS Block IIF Satellite MISSION OVERVIEW Copyright © 2016 United Launch Alliance, LLC. All Rights Reserved. The Atlas V 401 rocket has become the workhorse of the Atlas V fleet, delivering half of all Atlas V missions to date. In its nearly 14 years of service, the 401 has delivered 18 national security missions to orbit including five GPS satellites. The 401 rocket has also completed nine science and exploration flights, including two missions to Mars, a mission each to the sun and moon as well as a resupply mission to the International Space Station. First Launch: Aug. 21, 2002 Launches to date: 30 Performance to GTO: 4,750 kg (10,470 lb) Performance to LEO-Reference: 9,800 kg (21,600 lb) ing mission performance: stem operation. environments, Payload Fairing (PLF) The GPS IIF-12 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 con- structed of pressure-stabilized, corrosion resistant stainless steel. Centaur is a liquid hydrogen/liquid oxygen- (cryogenic-) fueled vehicle. It uses a single RL10C 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 The Atlas V booster is 12.5 ft in diameter and 106.5 ft in length. The booster’s tanks are structur- 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 Centaur avionics system, which provides guidance, flight control, and vehicle sequencing functions during the booster and Centaur phases of flight. With more than a century of combined heritage, United Launch Alliance is the nation’s most experienced and reliable launch service provider. ULA has successfully delivered more than 100 satellites to orbit that provide critical capabilities for troops in the field, aid meteorologists in tracking severe weather, enable personal device-based GPS navigation and unlock the mysteries of our solar system. Join the conversation: ULALaunch.com
  • 2. 2 3 1 Centaur Booster Interstage Adapter 4-m Payload Fairing Halves Spacecraft Mobile Launch Platform Payload Transporter Atlas Spaceflight Operations Center (ASOC) | Launch Control Center and Mission Director’s Center Spacecraft Processing Facility | Spacecraft processing, testing and encapsulation Vertical Integration Facility | Launch vehicle Integration and testing, spacecraft mate and integrated operations 1 3 2 4 4 6 7 5 9 2 5 3 8 1 10 Vertical Integration Facility (VIF) (See inset) Bridge Crane Hammerhead Bridge Crane Launch Vehicle Mobile Launch Platform (MLP) Centaur LO2 Storage High Pressure Gas Storage Booster LO2 Storage Pad Equipment Building (PEB) Pad ECS Shelter 1 4 5 3 2 6 7 8 9 10 Space Launch Complex 41 1 2 3 4 555 6 8 MISSION PROFILE AND GROUND TRACEATLAS V PRODUCTION AND LAUNCH Denver, CO – ULA Headquarters & Design Center Engineering Harlingen, TX – Payload Fairing, Boattail, Centaur Forward Adapter, Aft Stub Adapter, & Launch Vehicle Adapter Fabrication Decatur, AL – Booster Fabrication & Final Assembly, Centaur Tank Fabrication & Centaur Final Assembly West Palm Beach, FL – RL10C Engine Fabrication at Aerojet Rocketdyne Khimki, Russia – RD-180 Engine Fabrication at NPO Energomash 1 2 3 4 5 nter (ASOC) | LLaunch r er, & ion embly, taur rojet NPO Longitude (deg) GeodeticLatitude(deg) 80 60 40 20 0 -20 -80 -60 -40 -135 -90 -45 0 1359045 Telemetry Ground Station Launch Vehicle/Spacecraft Ground Trace TDRS Asset Geostationary Orbital Position ER Guam TDRS 041TDRS 046 BOSS LION Diego Garcia 5 6 7 8 All Values Approximate Time (hr:min:sec)Event 1 2 3 4 5 6 7 8 Time (seconds) RD-180 Engine Ignition -2.7 -00:00:02.7 Liftoff (Thrust to Weight > 1) 1.1 00:00:01.1 Begin Pitch/Yaw Maneuver 17.3 00:00:17.3 Mach 1 78.5 00:01:18.5 Maximum Dynamic Pressure 90.3 00:01:30.3 Atlas Booster Engine Cutoff (BECO) 243.9 00:04:03.9 Atlas Booster/Centaur Separation 249.9 00:04:09.9 Centaur Main Engine Start (MES-1) 259.9 00:04:19.9 Payload Fairing Jettison 267.9 00:04:27.9 Centaur First Main Engine Cutoff (MECO-1) 1,024.0 00:17:04.0 Centaur Second Main Engine Start (MES-2) 11,823.3 03:17:03.3 Centaur Second Main Engine Cutoff (MECO-2) 11,910.1 03:18:30.1 GPS IIF-12 Separation 12,196.1 03:23:16.1 Perigee Altitude: 11,047 nmi | Apogee Altitude: 11,047 nmi | Inclination: 55.0 deg | Flight Azimuth: 45.8 deg