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GPS IIF

SCHRIEVER AIR FORCE BASE, Colo. --  GPS IIF satellite. (USAF Graphic)

GPS IIF

MISSION

 

Deliver sustained, reliable GPS capabilities to America’s warfighters, our allies and civil users.  GPS provides positioning, navigation and timing service to civil and military users worldwide.

 

BACKGROUND

 

In 1996, the GPS IIF contract was awarded to The Boeing Company for the development and production of 33 space vehicles (SVs). In 2000 the United States Air Force modernized the contract, increasing capabilities and reducing the number of SV’s delivered to twelve. On 27 May 2010, the first GPS IIF satellite was launched from Cape Canaveral Air Force Station, Fla. On 5 February 2016, the last in a series of 12 satellites was launched from Cape Canaveral Air Force Station, Fla.

 

DESCRIPTION

 

GPS IIF SV’s continue to modernize the GPS constellation while bringing new capabilities to both military and civilian users. GPS IIF SV’s will bring into service the dedicated civil signal (L5) as part of the modernization effort that began with GPS IIR-M. GPS IIF also brings improved accuracy, greater security and anti-jam capabilities over previous blocks while maintaining baseline legacy GPS performance.

 

  • Development and Production Contract

  • Development of modernized GPS IIF is complete  

  • Delivered 12 SVs

  • Develop Ground Control System

     

  • Mission Support

  • Provide on-site vehicle launch processing and launch support at Cape Canaveral AFS

  • Monitor on-orbit GPS IIF satellites from Schriever AFB

  • Support 2 SOPS in day-to-day control and maintenance

  • Provide expertise in resolving anomalies/out-of-family conditions

 

CAPABILITIES

 

  • Next Generation of GPS satellites

  • Legacy signals:  L1 C/A, L1/2 P(Y)

  • Dedicated civilian signals:  L5I, L5Q

  • Multiple civil/military signals:  L1M, L2M, L2C

  • Improved anti-jam

  • Improved accuracy

     

GENERAL CHARACTERISTICS

  • Orbit:  Six orbit planes at 55 degree inclination

  • Altitude:  10,898 nautical miles

  • Design life:  12 years

  • On-orbit weight:  3,230 lb

  • Size:  98 in wide, 80 in deep, 88 in high

  • Position accuracy:  1.5 meters, with daily updates from the control segment 

  • Electrical Power Subsystem

  • Solar array:  3-Panel Improved Triple Junction GaAs Solar Arrays, 1900 watt capacity

  • Battery system:  NiH2, rechargeable

  • Attitude Determination and Control

  • Zero momentum, 3-axis stabilized, Earth-oriented, Sun-nadir pointing

  • Attitude reference control:  Static Earth sensor, Sun sensor, reaction wheels/magnetic coils

  • Propulsion Subsystem

  • Propellant:  Monopropellant N2H4

  • Propellant capacity:  320 lbs

  • Thrusters:  Twelve 1.0-lb REAs and four 5.0-lb REAs

  • Navigation Payload

  • Two Rubidium clocks & one Cesium clock, radiation-hardened design, high stability timing

  • RH32 central processor, ADA HOL, integral baseband processor, full message encoding and processing, real-time Kalman filter

  • Improved Crosslink performance with Narrow Band Crystal filter

  • Structure and Thermal

  • Structure:  Six aluminum honeycomb panels mounted to a central aluminum core

  • Thermal control:  Blankets, thermal coatings, radiators and electrically controlled heaters

  • Tracking, Telemetry and Command

  • S-band, SGLS transponder Security architecture:  Encrypted data links, redundant RH32 control processor, centralized command decoding and telemetry communications

 

PRIME CONTRACTOR:  The Boeing Company

 

(Current as of April 2018)