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Strategic missile 15P015 (MP-UR100) with rocket 15A15

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    Basing

    :

    Mine PU

    management system:

    management software

    Warhead:

    spetsboepripasov

    Application:

    Strategic

    Country:

    Russia

    Range:

    10320 km.

    year development:

    1975

    strategic missile 15p015 (mr-ur100) with rocket 15A15 Resolution of the Government of the USSR N 682-218 August 19, 1970. parent organizations - "Southern" and CDBMB - was set to develop projects for modernization of strategic missile complex UR-100, standing on alert. In accordance with this resolution, "Southern" was entrusted with the development of the missile complex intercontinental missile MR UR100 (15A15) with access to the flight tests in 1973. The objective was to modernize the complex UR-100 with minimal time and cost. UR-100 missile (8K84) easy class was developed CDBMB, entered service in 1967, the Strategic Missile Forces. Was relatively inexpensive and produced in large quantities for the early Soviet military build-up in the competition with the United States. There were about a thousand of missiles deployed. Due to obsolescence missiles UR-100 was necessary in the existing mine facilities to establish new, more modern and efficient intercontinental missiles. Development on a competitive basis stimulated rival organizations seek to improve the performance characteristics of the complex and boost the pace of work.

    Starting work on complex 15P015 in "Southern" coincided with the work on the creation of strategic missile complex "heavy" P-36M (15P014) with rocket 15A14. Intensive development of these two new complexes of the third generation design team carried out almost simultaneously. Complex with a rocket MR UR100 created about a year later and it gave to borrow new and promising design solutions of complex R-36M and thus shorten its mining. Both complexes were applied scheme mortar launch of the WPK, multiple warheads (MIRV), the control system based on digital computer, a single unified fighting unit similar design-layout circuits solid motors MIRV.

    high degree of continuity can accelerate mining 15A15 missiles. Flight tests of missiles and 15A14 15A15 began almost simultaneously.

    15P015

    Missile (MR-UR100) with 15A15 missile equipped with multiple reentry warhead, was adopted by the USSR Strategic Missile Forces in 1975. May 6, 1975 in Bologoe on duty was raised first missile regiment, armed with this missile system.

    Since 1979 began replacing parts 15A15 missile (MR-UR100) in deployed missile regiments on a modernized version - 15A16 (MR UR100UTTH). In the second half of the 80s it was decided on the gradual decommissioning of rockets of this family. By the time of the signing of the START-1 on duty there are only 47 units, and in 1995 the last of them were eliminated.

    the west range was designated SS-17 Mod.1, 2 (under START-1 - RS-16A);

    Composition

    strategic missile 15p015 (mr-ur100) with rocket 15A15 Two-stage ICBM easy class tandem circuit MR UR100 (see diagram) was performed in two diameters, increased compared with SD- 100: diameter of the first stage was 2.25m, the second - 2.1m. The steps were interconnected conical transition compartment, which was destroyed at staging elongated shaped charge (UKZ), herpes adapter section in the middle. This scheme has been applied for the first time in the development of "Southern". At both stages of fuel and oxidizer tanks were combined into a single fuel tank, intermediate bottom in which a sheet of trimetallic (AMg6 + + AMg6 AD1) with a secondary seal welds. For the manufacture of fuel tanks shells used more durable shell wafer manufacturing technology which was first mastered in relation to the R-36M.

    The rocket

    MR UR100 used so-called "chemical" pre-boost fuel tanks, as well as intakes of original design with destratifier ("agitators") provides minimum balances nezabora fuel in the tanks. Rocket fuel system was completely ampulizirovana, eliminating the need pnevmoispytany in operation areas.

    braking body second stage was carried out by separating warhead gazoreaktivnoy system by venting the boost pressure of the fuel compartment cavities. An autopsy was performed UKZ protivotyagi nozzles. The rocket was used the new system fuel consumption control (Surt) for simultaneous emptying fuel tanks and optimal use of fuel reserves, which resulted in a significantly improved energy missiles.

    The first stage was set marching single chamber engine (development KBEM) second stage of R-36M and managing four-chamber engine 15D167 developed KB Yuzhnoye SDO-4 on the basis of production engines 8D68 and 8D612. LRE 15D167 executed on an open circuit without afterburner, provided for the first stage, in addition to its primary function as the fuel tank pressurization reducing gas, food and fuel oxidizer unit oxidizer tank pressurization and power fuel system hydraulic drives, and for the second stage - the power components of fuel systems prior tank pressurization. Combustion chamber rocket engine nozzle 15D167 tubular structure was designed with the maximum degree of commonality with the engine brake control MSA 8D612 missile 8K69. To organize the main engine fuel tank of the first stage was carried out with a concave bottom.

    single chamber rocket engine of the second stage sustainer 15D169 closed circuit housed in a toroidal cavity of the fuel tank. Thrust vector control was carried out by injection of gas in the supercritical generating portion of the nozzle. For roll control four nozzles used, working from the gasifier TNA. LRE 15D169 obbespechival also boost the oxidizer tank of the second stage gas generated by the gas generator pressurization, and fuel tank - reducing gas generator selected after THA. The engine was developed based on the LRE 15D512 second stage of 8K99 with some improvements to enhance the reliability and increase the resource.

    For breeding

    BB HSR used solid-control 15D171 developed "Southern" and NGO "Altai" structurally-layout scheme which is similar to the control scheme and 15D161 15D221 MIRV missiles 15A14, and the difference in the main characteristics (operating margin of fuel total momentum thrust time) due to a smaller number of BBs. Programming traction was carried out by selecting the charge of solid fuel combustion in a conical socket housing. Nicking the burning surface charge time ensured a smooth decrease of thrust.

    autonomous control system, inertial developed based on a digital computer with automated measurement errors command devices and automatically enters the appropriate amendments to the flight plan for the minimum time after receiving a start command. The control system allows retargeting during prelaunch. SU is placed in a single sealed container, separated from the rocket and providing flight MIRV. This decision eliminated the device housings, the maximum to bring them closer together, reducing their weight and the weight of the cable network to provide the best conditions for the operation of the equipment and significantly reduce the size and weight of the instrument compartment. Sealed instrument compartment became the object of dual use: first in the missile during flight first steps, and then, after separation from the launch in conjunction with HSR, provided her flight and breeding BB.

    Strict limits on the length of the rocket led to the need for another innovation - have developed a special fairing with a folding tip of two half-shells, which, after the rocket left the silos were formed under the action of the spring drive and formed a sharp cone.

    As a result

    developed for MIRV missiles MR-UR-100 by mass level of perfection is an unsurpassed example of this day.

    warheads missiles

    MIRV 4 PFYAV resistant to BB with a charge of 0.4 Mt each;

    close coupled with MS-resistant PFYAV BB 3.4 Mt of charge

    missile systems (DBK) - stationary with protected from terrestrial YaV automated silo launchers and command post (CP). Start - mortar from TPK using PAD. Combat application provided at any time of year and day, in any weather conditions, as well as after exposure to nuclear explosion (within security DBK). Aiming rocket azimuth provides fully autonomous system (without using a ground survey network), the system uses automatic aiming gyro and quantum optical gyro placed in PU. Aiming system provides the primary definition of the base azimuth direction when setting missiles on alert and storing it in the process of alerting, including a nuclear impact on the launcher, and the restoration of basic azimuth direction after exposure.

    Composition DBK

    ten automated single launchers on existing PU "OS 84";

    unified manual shaft-type, container type;

    unified system of command and control and internal power supply.

    distance between adjacent PU, PU and its UKP DBK DBK neighboring flank PU - 6-8 km.

    In an embodiment of modernization

    PU "OS 84" proposed LACA (Chief Designer Utkin AF), the most preserved part of the silo construction and industrial production provided the main elements of the modified MSE (15P715) - protective device rotary type power metal cups, etc., with increased security facilities not less than 15raz. An important feature of the silo 15P715 was that silo launcher did not have electrical systems temperaturovlazhnostnogo regime and provided the necessary climate through solid insulation on the outer surface of the metal construction and a protective roof and double rubber germokontura perimeter of the roof. Inside the rocket launcher were only passive means of air drying - cassette with sorbent (calcium chloride), which were replaced with regulations.

    transport and launch container for the rocket 15A15 is a welded cylinder sizes 2h20m AMg6 aluminum alloy with a number of edges on the outside diameter. The complexity of manufacturing such a large size TPK was high precision machining to ensure that the internal cavity of tightness at the output of the rocket. Originally it was supposed to lead to the production of Omsk N 166 aircraft factory (later NPO "Flight"), but was subsequently appointed a new manufacturer TPK - Zhdanov plant "Tyazhmash".

    General Assembly rocket loading TPK, comprehensive inspection systems missiles and ground-launch screening equipment installed at TPK, at the factory. Overloading TPK with a missile at all stages of operation - Ros way in any weather conditions. Unpaved terrain vehicle with a rocket TPK delivered to the UE without inspection at a technical position. Loading TPK with a missile in PU - using the unified handling equipment. Refilling rocket fuel - using standardized vehicle traffic fueling equipment without the presence of personnel in the PU. Snapping to the rocket fully assembled and tested MS - using the unified for all kinds of combat equipment of transport and installation equipment.

    PERFORMANCE

    General Characteristics

    Sighting range, km:
    - Maximum with MIRV
    - Maximum with monobloc MS
    - Minimal


    10250
    10320
    1000

    Weapon Accuracy (at a distance of 10,000 km), km

    ± 1.6

    District breeding BB km

    200x100

    Combat readiness, with

    80

    Warranty period Spent on duty at Schedule 1 time in 3 years, years

    10

    Rocket 15A15

    Starting weight

    missiles, n

    71.2

    Weight warhead kgs

    2100

    Flight reliability

    0.957

    Diameter, m

    2.25

    Length, m

    22.51

    Features Control

    Link Control (on the ground / in a vacuum), tf:
    - I stage main engine
    - I stage steering engine
    - II stage


    117/126
    28/33
    - / 14.5

    Specific impulse control in a vacuum, with:
    - I stage
    - II stage


    318.5
    330.5

    tests and operation

    Flight kontsruktorskie missile test MR-UR-100 began at NIIP-5 under the guidance of the State Commission, headed by Colonel-General FP Fine and his deputy, Chief Designer Yuzhnoye SDO VF Utkin. Starting LCI - 1972., End - 1975.

    Total starts in the LCI - 40 of them:

    the district "Kura" - 32

    the district "Water area" - 7

    the minimum distance (in the district "Kyzyl-Tu") -1

    the number of emergency starts - 3

    number of partially successful launches -2.

    Total number of starts - 67 of them emergency - 7. Successful launches - 89.5%.





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