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History of the Titan 1 Rocket
The Titan 1 rocket (shown at right) was first developed in October 1955, when the US Air Force awarded the then Martin Company a contract to build an Intercontinental Ballistic Missile (ICBM). It was the United States’ first two stage rocket and formed an integral part of their strategic deterrent force. In the early 1960’s the rocket was adapted to launch the Gemini capsule that carried two people at a time into space. Titan succeed in launching 12 Gemini spacecraft and has also helped to launch the Viking missions to Mars, Voyager I and II and most recently Cassini to Saturn. Titan and the Gemini Space Missions
Titan 1 at Cape Canaveral, Florida On February 6, 1959, the first Titan Intercontinental Missile (ICBM) was successfully launched from Cape Canaveral Launch Complex 15. The 10 foot diameter Titan 1 rocket had two liquid-fueled stages, but may have had water in the second stage tanks for the first flight. During a period of five weeks, the rocket passed through four scrubs before it finally left the pad. As the rocket engine ignited, a discharge line in the engine from the liquid oxy gen tank came out and spewed on the engine and launch stand. As a result, hydraulic lines on the launch stand burst mixing liquid oxygen with hydraulic fuel. While the mixture was a formula for an explosion, the rocket left the stand, cleared the tower and when on to successfully accomplish the mission objectives. While the Atlas and the Titan were the first deployed US ICBMs, they also both served to transport men to space in the Mercury (Atlas) and Gemini (Titan) programs (Flatoday). Systems Operation The launch sequence took approximately 15 minutes. After receiving a launch order, the crew filled the missile's tanks with 200,000 pounds of liquid oxygen and RP-1. After the missile was fueled, it rode to the surface on the silo elevator and then was fired. The flight began with the ignition of the large first-stage engine that burned for 134 seconds and propelled the missile to an altitude of 35 miles. As the first stage expired and fell away, the second stage fired; it burned for another 156 seconds, boosting the missile to an altitude of150 miles and a velocity of 22,554 feet per second. After the second stage fen silent, two small vernier engines fired for an additional 50 seconds making final course corrections to the trajectory, After the vernier engines burned out, the reent6 vehicle carrying the war-head followed a ballistic trajectory, and at the apogee of its flight soared to an altitude of 541 miles above the earth's surface. Time elapsed for a 5,500 mile flight: 33 minutes. Developmental History The ICBM Scientific Advisory Committee planted the seeds of the Titan program in July 1954 when it recommended that the Air Force's Western Development Division's (WDD) explore alternate missile configurations before entrusting the nation entire ICBM program to the untested Atlas (SM-65). The following month the WDD directed its systems engineering and technical direction (SE/TD) contractor, the Ramo-Wooldridge Corporation, to institute a study of alternate ICBM configurations. Shortly thereafter the contractor hired Lockheed Aircraft Corporation and the Glenn L. Martin Aircraft Company to help with the task. The ICBM Scientific Advisory Committee was a group of prominent civilian scientists and engineers that advised the Air Force on the missile program. When the study began, both the WDD and Ramo-Wooldridge were leery of becoming overly reliant on Atlas. Convair's design reflected an unconventional approach, and while many tests had been made, it had not been flight tested nor could it be for nearly 3 years. Based on the preliminary results of its study, in October the WDD recommended that Convair go ahead with Atlas, but at the same time the development agency also suggested that the Air Force broaden its ICBM program to include a missile with rigid, aircraft type fuselage and an alternate engine configuration. The VV`DD stressed that developing a second ICBM would allow the Air Force to pursue a more ambitious design and would also stimulate competition between the two ICBM programs. In January 1955 the ICBM Scientific Advisory Committee reviewed the WDD's findings and recommended that the Air Force pursue an alternate ICBM configuration, most probably one with a two-stage propulsion system. Based on the committee's recommendation, in April 1955 Secretary of the Air Force Harold Talbott authorized the VV`DD to begin work on a second ICBM. His only stipulation was that the winning contractor agree to build its missile production facility in the central United States. The Air Force solicited bids for the second ICBM in May 1955 and the following October awarded the Glenn L. Martin Aircraft Company of Baltimore, Maryland a con-tract to develop the new Titan I (SM-68A) ICBM. Martin built its Titan production facility outside of Denver, Colorado. The Air Force accepted delivery of its first production Titan in June 1958, and began testing shortly thereafter. In April 1959 the Army Corps of Engineers began supervising the construction of the first Titan I launch facilities at Lowry AFB, Colorado. Three years later that site hosted the first Titan I squadron to be placed on operational alert. Site Configuration In 1956 the Air Force decided that all of the Titan I missiles should be based in super-hardened" silos buried deep underground. Using data from above-ground nuclear tests, the Air Force found that at a reasonable cost it could construct the launch facilities to withstand overpressures of 25 to 100 pounds per square inch (psi). Subsequently, all of the Titan I launch sites were built to withstand overpressures of 100 psi. The Army Corps of Engineers Ballistic Missile Construction Office (CEBMCO) began building the first Titan I launch facilities at Lowry AFB, Colorado, in May 1959. Each squadron consisted of nine missiles evenly divided among three launch complexes. The missiles were grouped in clusters of three because they had to remain close to their ground-based radars and guidance computers. The mammoth underground complexes were miniature cities, complete with their own power and water supplies. The entire complex was buried deep beneath the ground, and all the parts were linked by underground passageways. At one end of the complex were the three missile silos, each 160 feet deep and 44 feet in diameter. They were built of reinforced concrete that ranged in thickness from 2 to 3 feet. Within the silo was a steel framework that housed both the missile and the elevator that carried it to the surface. The only parts of the silo that protruded above the surface were two horizontal doors, each weighing 125 tons. Adjacent to each silo were the propellant storage and equipment terminal buildings, both of which were buried under 17 to 24 feet of earth. Several hundred feet away were the control room and power house. Both were domed structures built of reinforced concrete and buried 10 to 17 feet beneath the surface. The control room was 40 feet high,100 feet in diameter, and housed all of the launch control equipment. The nearby power house was 60 feet high, 127 feet in diameter, and contained generators and the power distribution system. Nestled between the two buildings was the cylindrical entry portal,72 feet deep and 38 feet in diameter, that controlled access to the underground complex. At the base of the complex were two radar antennas that were part of the missile's ground-based guidance system. The antennas were housed in two silos, each 67 feet deep and 38 feet in diameter. The launch crews raised tfie antennas above ground as they readied the missile for firing. The antennas were approximately 1,300 feet from the farthest silo. More than 2,500 feet of corrugated steel tunnel, 9 feet in diameter and buried 40 feet beneath the surface, connected all the buildings within the complex.
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Summary