.

Strategic missile UR-100N UTTH with rocket 15A35

BACK NEXT
    Basing

    :

    Mine PU

    management system:

    management software

    Warhead:

    spetsboepripasov

    Application:

    Strategic

    Country:

    Russia

    Range:

    10,000 km.

    year development:

    1979

    strategic missile UR-100N UTTH with rocket 15a35

    intercontinental ballistic missile liquid 15A30 (UR-100N) third-generation reentry warhead independently targetable (MIRV) developed under the direction of the CDB Engineering Chelomey. In August 1969 a meeting of the Defence Council, chaired by the USSR Leonid Brezhnev, which discussed the development prospects of the Strategic Missile Forces and the USSR were approved proposals "Southern" in modernization was already armed with missiles R-36M and UR- 100. This was not rejected and the proposed modernization of the scheme CDBMB UR-100, and in essence - the creation of a new missile system UR-100N. August 19, 1970 the Government issued a decree № 682-218 to develop missile system UR-100N (15A30) with "the heaviest rocket of light ICBMs" (this term was later adopted in the agreed contracts). Along with a set of UR-100N on a competitive basis with the IDB created complex MR-UR-100 (led Yangel). Complexes UR-100N and MR-UR-100 offered to replace the family ICBM light class of SD-100 (8K84), adopted by the Strategic Missile Forces in 1967 and deployed in large numbers (peak deployment was achieved in 1974, when the number of simultaneously deployed ICBMs of that type has reached 1030 units). The final choice between the IDB UR-100N and MR-UR-100 had to do after the comparative flight tests. This decision marked the beginning of what is in the historical and memoir literature devoted to Soviet rocket and space technology is called "dispute century." By its TTX complex UR-100N, with very advanced on the main technical characteristics rocket was between "light" MR-UR-100 and "heavy" R-36M, which, according to some participants and observers "dispute of the century", engendered at Chelomey hope not only that his rocket fails to win the competition with the MR-UR-100, but also the fact that it is cheaper and mass prefer comparatively expensive heavy R-36M. Such views, of course, are not separated Yangel. In addition, the government also considers essential to the defense of the USSR have in the Strategic Missile ICBM heavy class, so hope Chelomey to "spoofing" R-36M using the UR-100N did not materialize.

    For

    Chelomey complexity of creating a new rocket was and that refinement silo complex UR-100 rocket under the UR-100N, with its "hot" "gasdynamic start" virtually poured into a complete dismantling of the existing silos and construction of a new implementation of a full cycle of construction works (for hardening device mine needed a complete dismantling of the mine shaft, its terminal and the strong foundation, excavation to increase the diameter of the mine and the construction of a new concrete structure silos), because otherwise arise would be a real danger of some places in the flue gases of supersonic flow silos and jumps seals with a sharp change in its modes (pressure, temperature, heat transfer), leading to an emergency start a promising new rocket. Roughly speaking, from the old silos remained unchanged only the center line, while the proposed Yangel new and risky concept of "cold", "mortar start" for both his team developed missiles allowed actually do already built silos with necessary completions (it looked like a prudent use of already constructed silos, ie, as a more economical approach). When designing a new missile silo complex structures UR-100N testing of gas dynamics start was entrusted TsNIIMASH. Institute coped with this problem by placing a small-scale model. She was carried out with precise experiments and worked small vent devices. To reduce the unacceptably high levels of shock-wave pressure on missile UR-100N when run the engine at the bottom of the container, on the recommendation of the Institute was established specially designed duralumin screen. When lifting the missile shield under the influence of jets destroyed than to continue to ensure the ejection flow regime. However, despite the large amount of work demanded, according to U.S. intelligence silos OS 15P730 (then 15P730P, 15P735) held first place for resistance to PFYAV among other Soviet combat missile silo complexes until adopting ICBM -> < / p>

    strategic missile UR-100N UTTH with rocket 15a35

    ICBM 15A35 - two-stage intercontinental ballistic missile, made in a "tandem" with a serial stage separation (see diagram). The missile has a very compact layout and almost lack of "dry" sections.

    housing first stage consists of the tail, the fuel compartments and adapter. Fuel tanks - the supporting structure, with a common head. The propulsion system of the first stage RD-0234 (15D96) consists of four liquid rocket propulsion engines (LRE) RD-0233 (15D95) (see photo). Each motor is pivotally mounted on the frame in the tail section and may deviate from the neutral position in the corresponding plane. The engines have a turbo fuel system with staged combustion. The upper end of the first stage oxidizer tank has a complicated shape and comprises a conical portion directed towards the interior of the tank and the central spherical portion having the convexity outwards. In the space thus formed is placed sustainer rocket engine nozzle of the second stage. Aspiration tanks sustainer stages by means of hot gases. Separation of the first and second stage there is a "hot" scheme by the steering engine of the second stage, which started before the command to shut down the first-stage rocket engine. Exhaust gases working steering engine of the second stage are printed using a special system of windows in the building of the first stage. Then there is a break for the team of mechanical linkages between the stages, the first stage of withdrawal and start the main engine of the second stage. Inhibition of the first stage is carried out four solid braking engines mounted on the tail section.

    Housing

    second stage consists of a shortened tail and fuel compartments. Fuel tanks - the supporting structure. The propulsion system of the second stage includes marching RD-0235 (15D113) mounted fixedly and four-chamber steering engine RD-0236 (15D114) (see photo). Sustainer engine has fuel scheme with afterburning and steering - without post-combustion gas generator. Branch of the third stage of the second occurs at idle thrust rocket engine brake by solid second stage engines. Brake motors both sustainer stages designed in KB-2 plant number 81 under the direction of M. Kartukova. To the top of the second stage of the rocket body attached aggregate-instrument unit MIRV, which contains instruments inertial control system and the engine breeding warheads.

    warheads covered fairing. The missile is equipped with a set of decoys. Nuclear ICBM warheads UR-100N developed at SRI-1011 (now VNIITF Snejinsk Chelyabinsk region).

    UR-100N was adopted by two interchangeable with MS: "light" close coupled with thermonuclear warhead warhead capacity of 5.3Mt and MIRV 6 unmanageable BB capacity of each - 400kt (CHED - no more than 650 m at maximum range of 9650km) . Nuclear warheads for the UR-100N UTTH designed KB-11 (now VNIIEF, Sarov, Nizhny Novgorod region). UR-100N UTTH entered service with one embodiment of MS - MIRV 6 unmanageable BB capacity of each - 550 kt (CHED - no more than 350 m at maximum range 10,000 km). Combat equipment UR-100N allows UTTH confidently hit high security and defense system covered point and area targets. According to Western experts considered equipping version MIRV ICBM 15A35 new small-sized light BB spetszaryadov small class power that would increase if necessary by BB on one rocket to 18 units.

    Engine breeding RD-0237 (see photo) - liquid with pressure fuel system, without afterburning gas generator. Engine breeding and sustainer rocket engine first and second stages created KOKOSOKHIMMASH chemical automation led by AD Konopatov (Voronezh). In all stages of fuel used and nitrogen tetroxide unsymmetrical dimethylhydrazine. Development of these LRE and working out were carried out in 1969-1974 gg.

    management system developed at the Kharkov SRI-692 (later - NGO "Hartron") under the direction of G. Sergeeva. Installed on the rocket autonomous inertial control system with digital computer 15L579. Onboard computer complex unified with rocket ->

    firing range, km

    10000 (9 650 MIRV)

    Missile length

    24.3 (24.0 for 15A30)

    maximum body diameter, m

    2.5

    starting weight, t

    105.6

    Mass

    warhead kg

    4350

    CWE km

    0.35 (0.65)

    Warranty shelf life, years

    10 (15A35 extended for up to 33 years)

    control first stage
    - Thrust in vacuum, kN
    - Thrust at sea level, kN,
    - Specific impulse in a vacuum, with
    - Specific impulse at sea level, with
    - While working with


    2070
    1870
    310
    285
    121

    control second stage
    - Thrust in vacuum (marching), kN
    - Specific impulse in vacuum (marching), with
    - Time (marching), with
    - Thrust in vacuum (steering in conjunction), kN
    - Specific impulse in vacuum (steering), with
    - Time (steering), with


    240
    320
    183
    15.76
    293
    200

    tests and operation

    On the basis of the missile

    15A35 in Khrunichev. Khrunichev created conversion booster light class "Roar" (see photo), it starts with the state test conducted from the Plesetsk cosmodrome. RN "rumble" - three-stage rocket. First and second stage - ICBM missile unit UR-100N. As a third step is used booster "Briz". Missile length - 27.7 meters, diameter - 2.5 meters. Starting weight (without payload) - 107 tons. RN capable of outputting a payload of 1950 kilograms into orbit 200 kilometers or 1,250 pounds into orbit 1,500 kilometers. Relative mass of payload - 1,82%.

    Based 15A35 missiles in Mechanical Engineering NGO created space-rocket complex "Strela" (see photo), designed to be launched from the Baikonur space vehicles "Free" of the modernized silo 15P720 designed to launch rockets 15A20. The basic concept implemented in this project is to maintain maximum continuity KRK "Boom" to the base complex. Using space rocket complex "Arrow" will provide cost-effective launches of small satellites into orbits with different heights and inclinations. 15A20 missile smaller in size and energy than 15A35 missile. For this mine 15P720 deepens and intensifies its lower part. Geometry changes and the top of the silo like the top of the silo to install flue 15P735 lattice.

    tests and operation

    On the basis of the missile

    15A35 in Khrunichev. Khrunichev created conversion booster light class "Roar" (see photo), it starts with the state test conducted from the Plesetsk cosmodrome. RN "rumble" - three-stage rocket. First and second stage - ICBM missile unit UR-100N. As a third step is used booster "Briz". Missile length - 27.7 meters, diameter - 2.5 meters. Starting weight (without payload) - 107 tons. RN capable of outputting a payload of 1,950 pounds into orbit 200 kilometers or 1250 pounds into orbit 1,500 kilometers. Relative mass of payload - 1,82%.

    Based 15A35 missiles in Mechanical Engineering NGO created space-rocket complex "Strela" (see photo), designed to be launched from the Baikonur space vehicles "Free" of the modernized silo 15P720 designed to launch rockets 15A20. The basic concept implemented in this project is to maintain maximum continuity KRK "Boom" to the base complex. Using space rocket complex "Arrow" will provide cost-effective launches of small satellites into orbits with different heights and inclinations. 15A20 missile smaller in size and energy than 15A35 missile. For this mine 15P720 deepens and intensifies its lower part. Geometry changes and the top of the silo like the top of the silo to install flue 15P735 lattice.





BACK NEXT TOP

Site is a private collection of materials and is an amateur informational and educational resource. All information is obtained from public sources. The administration does not apply for authorship of the materials used. All rights belong to their owners