Strategic missile 15P016 (MR-UR-100UTTH) with rocket 15A16



    Mine PU

    management system:

    management software








    10200 km.

    year development:


    15p016 strategic missile (MR-UR-100utth) with rocket 15a16 Just a few months after adopting a complex with 15P015 15A15 missile (MR-UR100) August 16, 1976. Resolution of the Government of the USSR "Southern" was charged with the development of RK with improved performance characteristics. In December 1976. conceptual design of complex missile 15A16 received index was developed and presented to the customer.

    Modernization complex was designed to significantly increase the effectiveness of combat use with minimal rework and concerned mainly with multiple warheads and breeding stage. The first and the second stage used unchanged, and was replaced by a new stage dilution directly on seasoned rocket propellants, standing in silos. Project silo 15P716 high protection from terrestrial nuclear explosion has been developed under the guidance of LACA Utkin.

    Regular strategic missile with intercontinental missile 15P016 "easy" class 15A16 was adopted by 17 December 1980. Resolution of the Government of the USSR. The first regiment with 15A16 missile system has been put on alert October 17, 1978. By 1983, all the missiles 15A15 standing on duty in the amount of 130 units have been replaced by missiles 15A16. In addition, by reducing the UR-100 missiles were deployed 20 more missiles, bringing the total number of deployed ICBMs 15A16 150.

    Currently, all these missiles dismantled and all PU eliminated except one (Bologoe), which is left for museum purposes. Missiles were destroyed at the site Surovatikha (Nizhny Novgorod region.)


    15p016 strategic missile (MR-UR-100utth) with rocket 15a16 Launch 15A16 - intercontinental ballistic, liquid, two-stage, ampulizirovannaya. Fuel - liquid, hypergolic high boiling components (fuel - UDMH oxidant-AT). Rocket warheads - MIRV 4 resistant to the damaging factors of nuclear explosion warheads (BB) with a charge of 0.5 Mt each.

    Controls 1 stage - four-chamber rocket engine with rotary steering COP, II stage - the main engine, flight control pitch and yaw by using gas injection system in the supercritical part of the nozzle and special nozzle, running on generator gas and flight control roll < / p>

    Feature RK 15P016 that were used without modifications with RK 15P015 both stages rocket fairing and body TPK, making it possible to re 15A15 missiles, on combat duty in 15A16 without draining fuel components by replacing the warhead, the container with appliances and Verification SU-launching apparatus. This ensures the similarity of DBK, continuity and complete unification of most systems and assemblies in Kazakhstan 15P015.

    MIRV missiles 16F161 15A16 different from 15F154 MIRV missiles 15A15 modified solid engine breeding 15D171-02 with reduced traction spread through individual selection of critical sections nozzles. Introduced new momentumless Retention BB platform to undock and mechanisms of connectors between the BB and HSR.

    first time in the domestic rocket applied autonomous airborne system aiming "Meridian", which allows to determine with the help of self-orienting in the azimuth direction of the true meridian gyro platform and provides sighting after launch a nuclear strike on the launch pad. With the help of "Meridian" was possible to remotely measure and clarify the amendment azimuth base element defined at statement on combat duty with visual gyrocompass.


    TTX (combat use efficiency 1.5-2.5 fold) compared with 15A15 missile achieved through the application of new HSR BB with increased TNT equivalent (1.25 times), improved system management and control dilution MS, will improve accuracy rate the target 2 times. Management system - an autonomous, inertial, allowing to make retargeting during prelaunch.

    Technical operation

    rocket 15A16 15A15 missile identical operation. Launcher (15P716) - mine, automated, highly protected, such as "OS" - upgraded PU "OS-84." Terms alerting missiles - being in full combat readiness in silos. Way to 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 a nuclear explosion (within security DBK).


    General Characteristics

    Sighting range, km
    - Maximum
    - Minimal


    Weapon Accuracy km
    - In the absence of a nuclear strike the enemy at a starting position
    - At the start of the rocket after a nuclear strike on the starting position


    District breeding BB km


    Flight reliability


    Combat readiness, with


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


    Rocket 15A16

    Starting weight

    missiles, n


    Weight warhead kgs


    Dimensions, m:
    - Length
    - Diameter


    Features Control

    Traction control

    1 stage (on the ground / in a vacuum), tf:
    - The main engine
    - Steering engine


    Link Control 2 steps in a vacuum, n


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


    tests and operation

    15p016 strategic missile (MR-UR-100utth) with rocket 15a16 Flight tests began on 15P016 complex NIIP-5 in October 1977. and ended in September 1979. Given the fact that the first stage of the rocket remained unchanged volume was reduced LCI. Flight tests were conducted by the State Commission of the complex under the chairmanship of Major-General AF Dubovik. Basically, the emphasis was placed on testing of the new control system, new combat unit 15F162, to confirm the accuracy of shooting and testing process re missile system under the modified rocket. During flight tests were conducted 19 launches, 16 of them were successful. Causes alarm starts were mostly random manufacturing defects - improper functioning feedback loops steering gear pitch and yaw of the second stage due to the use of the contingency outlet jumper, nontransmission team on separation steps due to violation of connectors installed in violation of documentation. One of the triggers was the most serious consequences. As a result, errors in the recording of the flight task was not given a command to start the engine of the first stage. Rocket after launch mortar climbed 20m and collapsed into the launcher, which led to the complete destruction of the silo.

    Flight tests confirmed increasing the combat efeektivnosti complex is about 2.5 times compared with the complex 15P015 and allowed the State Commission to recommend it to the adoption.

    All launches were carried out with 5 NIIP. Starting LCI 1977. Closing LCI 1979.

    Total starts in the LCI:

    the district "Kura" 19

    the number of emergency starts 3

    the total number of starts: 25

    3 have emergency

    successful launch - 88%.

    5 July 1981. successfully completed the planned volume of tests PU 15P716 seismic loading air shock wave (test "Argon-4" CPM-III). Seismic sensors registered design loading, and the foundations were shifted F-1 and F-2 building structure (foundation for the support Installer), destroyed the base member has failed one entry RBU. No damage, deformation elements and equipment for silo was not. In 1984. PU 15P716 be subjected to high mechanical stress. Test Equipment launcher survived.


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