page_title: Titan IV
section_title: General characteristics
hierarchical_section_title: Titan IV / Vehicle description / General characteristics
caption_attribution_description: English: Bottom of First Stage of Titan IVB rocket, showing the two nozzles of the LR87 rocket engine (regarded as a single engine). Seen at the Evergreen Aviation &amp; Space Museum in McMinnville, Oregon.
context_page_description: Titan IV was a family of heavy-lift space launch vehicles developed by Martin Marietta and operated by the United States Air Force from 1989 to 2005. Launches were conducted from Cape Canaveral Air Force Station, Florida and Vandenberg Air Force Base, California.
  The Titan IV was the last of the Titan family of rockets, originally developed by the Glenn L. Martin Company in 1958. It was retired in 2005 due to their high cost of operation and concerns over its toxic propellant fuels, and replaced with the Atlas V and Delta IV launch vehicles under the EELV program. The final launch from Cape Canaveral occurred on 29 April 2005, and the final launch from Vandenberg AFB occurred on 19 October 2005. Lockheed Martin Space Systems built the Titan IVs near Denver, Colorado, under contract to the US government.
  Two Titan IV vehicles are currently on display at the National Museum of the United States Air Force in Dayton, Ohio and the Evergreen Aviation and Space Museum in McMinnville, Oregon.
context_section_description: Builder: Lockheed-Martin Astronautics
  Power Plant:
  Stage 0 consisted of two solid-rocket motors.
  Stage 1 used an LR87-AJ-11 liquid-propellant rocket engine.
  Stage 2 used the LR91-AJ-11 liquid-propellant engine.
  Optional upper stages included the Centaur and Inertial Upper Stage.
  Guidance System: A ring laser gyro guidance system manufactured by Honeywell.
  Thrust:
  Stage 0: Solid rocket motors provided 1.7 million pounds force (7.56 MN) per motor at liftoff.
  Stage 1: LR87-AJ-11 provided an average of 548,000 pounds force (2.44 MN)
  Stage 2: LR91-AJ-11 provided an average of 105,000 pounds force (467 kN).
  Optional Centaur (RL10A-3-3A) upper stage provided 33,100 pounds force (147 kN) and the Inertial Upper Stage provided up to 41,500 pounds force (185 kN).
  Length: Up to 204 feet (62 m)
  Lift Capability:
  Could carry up to 47,800 pounds (21,700 kg) into low Earth orbit
  up to 12,700 pounds (5,800 kg) into a geosynchronous orbit when launched from Cape Canaveral AFS, Fla.;
  and up to 38,800 pounds (17,600 kg) into a low Earth polar orbit when launched from Vandenberg AFB.
  into geosynchronous orbit:
  with Centaur upper stage 12,700 pounds (5,800 kg)
  with Inertial Upper Stage 5,250 pounds (2,380 kg)
  Payload fairing:
  Manufacturer: McDonnell Douglas Space Systems Co
  Diameter: 16.7 feet (5.1 m)
  Length: 56, 66, 76, or 86 ft
  Mass: 11,000, 12,000, 13,000, or 14,000 lb
  Design: 3 sections, isogrid structure, Aluminum
  Maximum Takeoff Weight: Approximately 2.2 million pounds (1,000,000 kg)
  Cost: Approximately $250–350 million, depending on launch configuration.
  Date deployed: June 1989
  Launch sites: Cape Canaveral AFS, Fla., and Vandenberg AFB, Calif.
caption: Bottom of first stage of Titan IVB rocket
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