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Titan II

Titan II
MK6 TITAN II.jpg
An LGM-25C Titan intercontinental ballistic missile in silo, ready to launch
Function ICBM/Launch vehicle
Manufacturer Martin
Country of origin United States
Cost per launch $3.16 million (1969)
Size
Height 31.394 m (103.00 ft)(ICBM config)
Diameter 3.05 m (10.0 ft)
Mass 154,000 kg (340,000 lb)
Stages 2
Capacity
Payload to LEO 3,600 kg (7,900 lb)
Payload to
100 km (62 mi) sub-orbital trajectory
3,700 kg (8,200 lb)
Payload to
Polar LEO
2,177 kg (4,800 lb)
Payload to
Escape
227 kg (500 lb)
Launch history
Status Retired
Launch sites Cape Canaveral
LC-15, LC-16 & LC-19
Vandenberg Air Force Base
LC-395 & SLC-4E/W
Total launches 106
ICBM: 81
GLV: 12
23G: 13
Successes 101
ICBM: 77
GLV: 12
23G: 12
Failures 5 (ICBM: 4, 23G: 1)
First flight 12 March 1962
Last flight 18 October 2003
Notable payloads Gemini (manned)
Clementine
First stage
Engines 1 LR-87
Thrust 1,900 kN (430,000 lbf)
Specific impulse 258 s
Burn time 156 s
Fuel Aerozine 50/dinitrogen tetroxide
Second stage
Engines 1 LR91
Thrust 445 kN (100,000 lbf)
Specific impulse 316 s
Burn time 180 s
Fuel A-50 Hydrazine/dinitrogen tetroxide

The Titan II was an intercontinental ballistic missile (ICBM) and space launcher developed by the Glenn L. Martin Company from the earlier Titan I missile. Titan II was originally designed and used as an ICBM, but was later used as a medium-lift space launch vehicle to carry payloads for the United States Air Force (USAF), National Aeronautics and Space Administration (NASA) and National Oceanic and Atmospheric Administration (NOAA). Those payloads included the USAF Defense Meteorological Satellite Program (DMSP), the NOAA weather satellites, and NASA's Gemini manned space capsules. The modified Titan II SLVs (Space Launch Vehicles) were launched from Vandenberg Air Force Base, California up until 2003.

The Titan II ICBM was the successor to the Titan I, with double the payload. Unlike the Titan I, it used hydrazine-based hypergolic propellant which was storable and reliably ignited. This reduced time to launch and permitted it to be launched from its silo. Titan II carried the largest single warhead of any American ICBM.

The missile consists of a two-stage, rocket engine powered vehicle and a re-entry vehicle (RV). Provisions are included for in-flight separation of Stage II from Stage I, and separation of the RV from Stage II. Stage I and Stage II vehicles each contain propellant and pressurization, rocket engine, hydraulic and electrical systems, and explosive components. In addition, Stage II contains the flight control system and missile guidance set.

The airframe is a two-stage, aerodynamically stable structure that houses and protects the airborne missile equipment during powered flight. The missile guidance system enables the shutdown and staging enable relay to initiate Stage I separation. Each stage is 10 feet (3.0 m) in diameter and has fuel and oxidizer tanks in tandem, with the walls of the tanks forming the skin of the missile in those areas. External conduits are attached to the outside surface of the tanks to provide passage for the wire bundles and tubing. Access doors are provided on the missile forward, aft and between-tanks structure for inspection and maintenance. A man-hole cover for tank entry is located on the forward dome of each tank.


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