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Initial Operational Capability (IOC):
Origin: United States of America
Parent System: Titan
Initial Operational Capability (IOC): 1955
Total Production: ?
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Description: The Titan launch vehicle evolved from Titan, the first US two-stage Intercontinental Ballistic Missile (ICBM). The Titan II launch vehicle inherited structural design and propulsion system from Titan I ICBM. These launch vehicles were charged to put into orbit the heaviest satellites and other US government's payloads. Titan III evolved from Titan II. Thereafter Lockheed-Martin developed the Titan IVA and the Titan IVB from the Titan III launch vehicle.
The Titan IVB is the largest, most powerful and heaviest expendable launch vehicle operated by the United States and provides critical space access for strategic payloads such as Milstar and DSP military satellites and heavyweight commercial satellites. It is capable of placing payloads of 47,800 lb (21,682 kg) into low-Earth orbit or more than 12,700 lb (5,760 kg) into geosynchronous orbit.
The Titan IVB propulsion system consists of two side solid propellant boosters which provide 1.7 million pounds of thrust each, and one two-stage (first stage LR87 548,000 pounds of thrust and second stage LR91 105,000 pounds) liquid propellant core motor. In addition, the Titan IV can accommodate the upper stage Centaur motor.
The Titan IVB launch vehicle was the last member of the Titan family and it was the only Titan-launch vehicle model being operated by the United States Air Force in the early years of the 21st century. Titan IVB along with the space shuttle were the platforms of choice to put into orbit the heaviest US government payloads.
The US Air Force launched the final Titan IV rocket carrying a national security payload from Vandenberg Air Force Base in California. This launch was performed on October 19, 2005, ending the Lockheed Martin's Titan space launch system career. In all, 39 Titan IV rockets have been launched throughout the program's life cycle.
Titan IVB Specifications
Number of Stages: 2
Height: 62 meter (2,448 inch)
Rocket Diameter: 3.20 meter
Max Lift-off Thrust: 3,400,000 pound (1,542 ton)
Max Lift-off Weight: 998 ton (2,200,176 pound)
Payload to GEO: 5,760 kilogram (12,698 pound)
Payload to LEO: 21,682 kilogram (47,800 pound)
CEP: Circular Error Probable
Meters (m) Kilometers (km) Nautic Miles (nm) Inch (in) Yard (yd) Foot (ft) Millimeter (mm)
Pound (lb) Kilogram (kg) kN (KiloNewton) Ton (t)
Meters per Second (mps) Kilometers per Hour (kph) Knot (kt) Miles per Hour (mph)
Liter (l) Galon (gl)
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