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Intercontinental ballistic missile HGM-25A Titan-1

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    Basing

    :

    Mine PU

    management system:

    management software

    Warhead:

    spetsboepripasov

    Application:

    Strategic

    Country:

    U.S.

    Range:

    11300 km.

    year development:

    1962

    intercontinental ballistic missile hgm-25a titan-1 The genealogy ICBM" Titan-1 "is from January 1955, when the U.S. Air Force decided to" duplicate "was already created when the first American ICBM" Atlas " by selecting another group of main contractors, as well as through the use of a core set of design solutions - primarily through the use of serial communication circuit stages, as well as through the use of standard type design scheme missiles (with power set housing). The study of this concept began in July 1954 under the authority of the Scientific Advisory Committee on the establishment of an ICBM (The ICBM Scientific Advisory Committee). This concept was generally welcomed the General Headquarters of the U.S. Air Force in April 1955, and in October 1955, after considering a number of options, the contractor for the development of the rocket itself and some of its systems, the company was named "Glenn L. Martin Aircraft Company "(later" Martin Marietta "). She was named the main contractor for the project as a whole. Then the rocket got its own name "Titan" and the designation SM-68A (in 1962, after the change of notation in the U.S. Air Force missile was designated HGM-25A). Development of both engines sustainer stages was entrusted the company "Aerojet General Corporation". Radioinertsialnaya guidance system is being developed by "Bell Telephone Laboratories" and "Remington Rand UNIVAC". Warhead development was entrusted company AVCO. Development of the program was conducted in the framework of a weapon system WS-107A-2. In October 1957, after the Soviet Union launched the first Sputnik, it was decided to accelerate the deployment of 4 squadrons data ICBMs but quickly decided to increase this number up to 12. However, in 1960, after the start of the research and development work on the ICBM "Titan-2" (to create virtually the same group of contractors using scientific and technical groundwork for ICBM "Titan-1") was decided to reduce the number of squadrons deployed ICBM "Titan-1" up to six.

    first launch of a new ICBM took place in February 1959 (Patrick AFB, FL), the second stage march was filled with water instead of fuel components, and instead of the standard warhead was used detachable part of the layout. First division stages (the second stage was still prototyping) was conducted during the fourth run. The first successful launch of the second stage with the standard and the capsule with telemetry equipment instead of MS was conducted in February 1960. The first successful launch with the standard MS was held in August of the same year. December 2, 1960 the first squadron was activated, which included combat duty had to get new ICBMs. A day later, with Vandenberg Air Force Base, using a prototype stationary missile systems, the first attempt to launch an ICBM "Titan-1" from the West Coast (unsuccessful silo was destroyed by the explosion was not subsequently recovered). The first successful launch of a new ICBM using landline complex structures DBK was performed with Vandenberg Air Force Base in May 1961. The first squadron, which had armed with new missiles (ICBMs 9), embarked on alert duty in April 1962 (Lowry AFB, Colorado). By October 1962 to be on duty on the new military equipment have also begun Squadron at airbases Lauri (9 ICBM, so this has become the largest airbase positional area with 18 data IDB), Mountain Home (Idaho, 9 ICBM), Beale (California, 9 ICBM), Larson (Washington, 9 ICBM), Ellsworth (South Dakota, 9 ICBM). Also at Vandenberg Air Force Base (CA) was deployed ICBMs with one DBK this type (3 silos), but according to the U.S. sources, data silos are not used for combat duty, which is very doubtful.

    ICBM "Titan-1", as well as other first-generation ICBMs were not safe to use - in different years (when trying to start and during charging process) explosions destroyed two starting positions (MSE). One of them was later restored.

    Successful testing and deployment of ICBMs second generation led to the fact that in May 1963 the Air Force Headquarters approved the removal from duty of a number of the first generation of ICBMs (including "Titan-1") in the period from January 1965 to In December 1968 it was decided to further accelerate this process - in 1964, Secretary of Defense McNamara announced a plan (known as "Project Added Effort"), according to which a large part of the first generation of ICBMs (except "Atlas-F") was shot with alerting to December 1965. In November of the same year plan "Project Added Effort" was extended to all of the first generation of ICBMs, the removal of which alerting it was decided to further accelerate - the last of the first generation of ICBMs, it was decided to de-alert by the end of June 1965 First ICBM " ; Titan-1 "have been removed from duty in January 1965, and in March of the same year, the latest launch of the ICBM. Last ICBM "Titan-1" has been removed from combat duty in April 1965, in June of the same year, the squadron was deactivated last data ICBM (Lowry AFB, Colorado). Short history of ICBM "Titan-1" came to an end - on alert missiles stood only three years. All deactivated missiles were impounded at the air station Miro Loma (California).

    ICBM "Titan-1" after deactivation is not used (in contrast, for example, from an ICBM "Atlas" or "Titan-2") as an RN or for research starts - a year after deactivation in April 1966, all impounded missiles were scrapped and their parts used in the future for various experiments in the world. Total 155 missiles were produced, of which 70 were used in launches (17 launches were unsuccessful). In the period when on duty ICBM "Titan-1" was used for a number of test runs, especially for developing a number of promising systems ICBM "Titan-2" - inertial navigation system, the PCB ABM gasdynamic start of the heavy liquid ICBM silos. "Titan-1" was also used in the test program early American missile defense systems.

    Composition

    intercontinental ballistic missile hgm-25a titan-1 intercontinental ballistic missile" Titan-1 "is designed as a two-stage rocket (see diagram), steps which have been linked to the longitudinal scheme. The fuel tanks of both rocket stages had the supporting structure and the work of the panels, made of a special, lightweight and high-strength aluminum alloy 2014 with a touch of copper. In the manufacture of the panels of the alloy tanks used at the time a unique molding equipment and the press. The resulting billets were subjected to chemical milling, and the assembly of panels carried out arc welding with tungsten electrode in inert gas.

    the first stage rocket engine was installed LR87-AJ-1, which had two combustion chambers of special steel with an independent supply of fuel components. As fuel both stages special missile missiles used kerosene RP-1, as an oxidizer - liquid oxygen. The combustion chambers were fixed on a special steel frame. For missile control pitch and yaw channels at the work site of the 1st stage of the combustion chamber could deviate in their hangers at angles up to 5 °. Roll control at the work site of the 1st stage was carried out. Each combustion chamber is equipped with independent turbopump assembly (TNA). TNA includes fuel and oxidizer pumps, gear and two balanced turbine. Switching off the engine of the first stage was carried out using a special sensor response, registered the pressure drop in the combustion chambers, then the control system generates a signal to activate the second stage of the power plant. Separation stages produced by the so-called. "Cold" scheme, ie, when broken propulsion stage 2. 2nd stage leads away from the first at a distance of 4.5 m with a 2-SRBs low thrust, which also provides the fuel pellet.

    The second stage was set a single-chamber rocket engine LR91-AJ-1 on a special steel frame. For missile control pitch and yaw channels at the work site of the 2nd stage combustor could deviate in its suspension at an angle of 3 °. Roll control at the work site of the 2nd stage was carried out by four special nozzles using gasifier gas. Turning off the power plant of the second stage was carried out using a special sensor response, registered the drop in pressure in the combustion chamber of the main engine, and then the control system generates a signal to switch the power plant exact trajectory correction.

    Powerplant exact trajectory correction consists of a two fluid motor launch which was produced at the same time for the final corrections for altitude and speed. After finishing their work (working time to 50 seconds) produced pirozamkov operation, hold the head part. Further comprising a block engines slip and breakdowns PCB defense. Block engines disposal consisted of two solid engine that ran consecutively. With their help stage moves away from MS.

    missile was equipped with monobloc thermonuclear warhead, is a combat unit Mk4 ablative heat-resistant type and warhead W-38 capacity of 4.5 Mt. To increase the likelihood of overcoming potential enemy missile missile missile was completed PCB consisting of light inflatable decoys. For the period beginning 60s such IRT PRO was quite an achievement. Radioinertsialnaya control system provides CWE no more than 2.2 km.

    intercontinental ballistic missile hgm-25a titan-1 Launch Complex for the ICBM" Titan-1 "was a real underground city, which has no analogues so far. At one end of the territory were located three silos size 49 * 13.5 meters each, constructed of heavy concrete with a thickness of 0.6 to 0.9 m design of the mine (see diagram) withstand overpressure in the shock front of a thermonuclear explosion to 10.5 kgf/cm2 (for DBK deployed on Vandenberg Air Force Base, on the complexes are deployed in position areas, this value was increased to 14 kgf/cm2). Immediately before the start of the rocket in already Wet rose from the mine to the surface using a special lift, thereby reducing its vulnerability to a sudden attack of the enemy. The mine was closed a couple of reinforced doors weighing 125 tons each. Next to each underground mine (at a depth of 5.2 to 7.3 m) were the premises for the storage of fuel components, as well as additional equipment room.

    A few dozen meters away from these facilities underground (at a depth of 3 to 5.2 m) were command posts and additional energy (where the diesel generators and batteries), both had a hemispherical shape. EP size - 30.5 * 12.2 m, the point size of the additional energy - 38.7 * 18.3 m between these structures was the entrance to the complex (with the roof at ground level), size 22 * 11,6 m On the opposite to the end of the silo complex were two mines, which housed the antenna control system and tracking of ICBMs. The size of each mine - 20.7 * 11.6 m before the start of the cover data mines opened and pushed to the antenna surface. The distance between the most distant from each other with ICBM silos and mine with the antenna does not exceed 400 meters between all underground structures were built steel tunnels total length of about 760 m They had a diameter of 2.7 m and were installed in 12 meters underground. The staff consisted of one DBK 10 people.

    PERFORMANCE

    firing range, km

    11300

    length assembly, m

    29,9

    diameter of the first stage, m, m

    3,05

    length of the first stage, m

    16

    diameter of the second stage, m, m

    2,26

    length of the second stage (without adapter for MS and MS), m

    9,8

    launch mass, m

    105,2

    GVW 1st stage, t

    76,2

    GVW 2nd stage, t

    27,2

    Weight empty stage 1, t

    4

    Weight empty stage 2, t

    1,73

    weight warheads (MS PRO + PCB), t

    1,8

    Link

    1st stage at sea level, kN

    1296

    Link

    1st stage in a vacuum, kN

    1468

    specific impulse stage 1 at sea level, with

    256

    Specific impulse

    1st stage in a vacuum, with

    290

    Hours 1st stage, with

    138

    Link

    stage 2 in vacuo, kN

    356

    Specific impulse

    2nd stage in vacuo to

    308

    Hours 2nd stage, with

    225

    apogee trajectory MS, km

    1300

    Power MS, MT

    1,45

    CWE MS, km

    2,2





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