Battle railway missile system 15P961 done with 15ZH61 ICBM (RT-23 UTTH)



    Railway PU

    management system:

    management software








    11000 km.

    year development:


    Battle railway missile system 15p961 done with 15zh61 ICBM (RT-23 UTTH) Work on the creation of the movable rail combat missile system (BZHRK) intercontinental ballistic missiles (ICBMs) started in the mid-1970s. Originally designed with a missile complex RT-23 is equipped with a single warhead. After testing with BZHRK ICBM RT-23 was adopted in trial operation.

    Resolution of the CPSU Central Committee and the USSR on August 9, 1983 was set to develop a missile with a missile complex PT 23UTTH "Good" (15ZH61) in three areas: a battle rail, road-mobile "Celina-2" and mine. Head developer - "Southern" (Chief Designer VF Utkin). In November 1982, has been developed preliminary design of rocket and PT 23UTTH BZHRK with improved rail launchers (ZHDPU). In particular, for shooting from any point of the route, including electrified railways, BZHRK was equipped with high-precision navigation system and ZHDPU - special devices and removing the shorting contact network (ZOKS).

    Complex adopted by the November 28, 1989.

    in 1987-1991 were built 12 complexes.

    In 1991, the NGO "Southern" proposed the use of rocket-type RT 23UTTH to launch spacecraft into Earth orbit with an altitude of 10 kilometers, after resetting the special rocket parachute system with heavy transport aircraft AN-124-100. Further development of this project has not received. Currently complex withdrawn from service.

    the west rocket PT 23UTTH (15ZH61) received the designation SS-24 "Ssalrel" MOD 3 (PL-4).

    Name START-1 - RS-22B, the classification of the START-1 - assembled ICBM launch container (Class A)


    Battle railway missile system 15p961 done with 15zh61 ICBM (RT-23 UTTH) The composition of the train enters BZHRK standard for complex configuration:

    trehvagonnyh three ICBM launchers module PT 23UTTH;

    command module consisting of 7 cars;

    tank wagon with supplies of fuels and lubricants;

    two locomotive DM-62.

    Each of the locomotives is on duty separate locomotive crew. In preparing the locomotive crews BZHRK officer, for details on the route, they periodically seconded civilian convoys IPU, following the same route.

    BZHRK looks like a normal part of the refrigerator and passenger cars. Launchers modules have eight wheelsets. Other cars - providing carriages are four pairs of wheels.

    Rocket PT 23UTTH (see diagram) has three stages plus stage dilution warheads. First, second and third stages have tselnomotanny body type "cocoon" of the composite material. The first stage is equipped with a solid engine 15D206 (borrowed from a rocket 15ZH44) with a central fixed, partially recessed nozzle running on mixed fuel T9-BK-8E. The second and third steps are also solid propulsion nozzle - central stationary, sliding. Fuel second stage - "Start", the third - AP-65. Management of the first stage is carried out blowing hot gases in the supercritical part of the nozzle of the propulsion system, the second - the deviation of the head portion and partially aerodynamic control surfaces mounted on the nose cone.

    head part - partial type with ten independently targetable warheads (BB) capacity 0.43Mt placed in one layer. Combat level (BS) equipped with multifunctional liquid rocket engine 15D264 (RD-866) running on dinitrogen tetroxide and unsymmetrical dimethylhydrazine (UDMH + AT). Multifunctional without afterburning engine generator gas 15D264 (RD-866) contains a single-chamber rocket engine thrust large (LRE BT), sixteen low-thrust rocket engine (LRE MT), and centralized power supply, consisting of two units with a turbopump gas generators and two feeders. RD-866 provides multiple switch and traction control LRE LRE BT and MT. Engine running on a combined scheme (exclusion and pump supply fuel components) and provides power propellants consumers in a wide range of flow and pressure. The maximum total time of LRE BT - 330c, LRE MT - 1200C. Maximum number of inclusions LRE BT - 14, LRE MT - 10000.

    The RD-866 is designed to perform the following tasks:

    creating control efforts to roll in flight combat stage;

    created (in the area of breeding) and traction control efforts, different in magnitude and direction, with multiple inclusions LRE LRE BT and MT;

    supply fuel hydrodrives swing cam engine big thrust in the area of breeding.

    Branch combat stage (BS) occurred on the classical "push" scheme. After separation of the LRE BT deduced stage combat at a given point of space rocket engine MT BS unfolded platform ahead and step dovorachivat detachable warheads (BB) down. After triggering squibs fastening and disconnect the main plug connector happened bezimpulsnoe office BB. After separating warhead LRE MT withdrawn BS aside and unfolded stage platform to run back LRE BT, which displays the BS point separating the next BB. The procedure was repeated for each combat unit. Thus by a complicated combination model using breeding and pulling and pushing schemes. Sited breeding (presumably) was carried out not by a rigid program (1 to 10), while the probability that the enemy would be impossible to calculate the breeding scheme.

    The rocket

    15ZH61 saved spent on rockets and 15ZH44 15ZH52 schematics and design solutions for mission control II and III stages deviation brain compartment mortar separation steps, the separation stage combat and breeding elements warheads. Mortar separation stages is provided by gas pressurization of the powder pressure accumulator mezhstupennogo volume and cross-division transfer compartment elongated shaped charge. This design ensures bumpless separation stages and provides maximum density mezhstupennoy layout of the rocket.

    Battle railway missile system 15p961 done with 15zh61 ICBM (RT-23 UTTH)

    rocket fairing has the original head of variable geometry. Metal corrugated insert under internal pressure created special accumulator pressure in flight straightened, getting a cone of revolution. This solution is applied to reduce the overall length of the missile and its placement in the car.

    management system - inertial with onboard digital computer (OBC) developed AP NGOs under the leadership of VA Lapygina.

    feature of the system is the management solution of a number of new tasks:

    recovery of information in the computer after the nuclear explosion by rewriting it in the random access memory of the custodian of information on a magnetic disk;

    implementation of the principles of terminal guidance;

    Use element base increased resistance to the effects of a nuclear explosion (Level 1);

    interfacing with the system command and control "signal A".


    by using terrestrial gyrocompass and electron-optical media azimuth gyrostabilized airborne platform.

    Launcher (see diagram) 15P761 developed KB Special Machinery (LACA) under the leadership of Utkin AF based chetyrehtelezhechnogo eight-carriage carrying capacity of 135 tons. Transport and launch container (TPK) is equipped with automatic temperature control and a missile launch. TPK rise to a vertical position is performed using pneumatic PAD'a. Wagon - launcher equipped with an opening roof with hydraulic drive and device for removing a contact network. Even mass reduction missiles at 1.5 tonnes compared to mine one is not allowed to meet the allowable axial load on the way. To resolve this problem, apply special "handling" of the device, redistributing the weight to neighboring cars.


    missiles can be carried out from any point of the route. For this composition stops, a special device is put aside catenary. Starting container rises to a vertical position. Then carried out a mortar rocket launch. Already in the air missile zaklonyaetsya using powder accelerator and only then starts boosters. Zaklonenie allowed to withdraw missiles jet propulsion engine from starting complex and ensure its sustainability.

    Each of the three launchers included in BZHRK can start to implement as part of the train, and off-line.

    Guaranteed storage life

    rocket 15 years.


    firing range, km


    Weapon Accuracy (deviation limit), km


    Starting weight, t


    Flight reliability


    ratio energovesovogo perfection rocket Gpg / Go, kgf / mc


    Missile length
    - Full
    - Without the head portion
    - TPK


    first stage
    - Length, m
    - Diameter, m
    - Weight, t
    - Joint control (on the ground / in a vacuum), n


    second stage
    - Length, m
    - Diameter, m
    - Joint control, n


    third stage
    - Length, m
    - Diameter, m
    - Joint control, n


    payload weight, kg


    Power charge, Mt

    10 x 0.43

    Liquid rocket engine RD-866 (combat level)

    engine thrust in vacuum, kg

    from -94.4 to +513.5


    average integral thrust impulse LRE BT in a vacuum, with kgf / kg


    Specific Impulse Vacuum Thrust, kgfs / kg
    - LRE chamber BT
    - LRE MT continuously
    - LRE MT in pulsed mode with a frequency of 10 Hz


    - weight, kg


    absolute gas pressure in a combustion chamber kgf/cm2:
    - LRE BT
    - LRE MT


    absolute gas pressure at the nozzle chamber, kgf/cm2:
    - LRE BT
    - LRE MT


    The weight ratio of the average integral

    fuel components at work:
    - LRE BT
    - LRE chamber BT
    - LRE MT


    deviation from nominal thrust, kgf
    - For LRE BT
    - For the LRE MT in continuous mode

    ± 41
    ± 0,65

    minimum absolute pressure of the fuel components at the engine inlet, kgf/cm2:
    - An oxidant (at 45 ° C)
    - Fuel (65 ° C)


    minimum absolute pressure of the fuel components at the engine inlet temperature +35 ° C, kgf/cm2:
    - Oxidant
    - Fuel


    Maximum cumulative work with:
    - LRE BT
    - LRE MT


    Max inclusions:
    - LRE BT
    - LRE MT



    Dimensions, m:
    - Length
    - Width
    - Height


    speed, km / h


    BZHRK Resistance to the shock wave, kg/cm2
    - Longitudinally
    - Laterally


    tests and operation

    Battle railway missile system 15p961 done with 15zh61 ICBM (RT-23 UTTH) Flight tests missiles PT 23UTTH (15ZH61) made from 27 February 1985 to 22 December 1987 in NIIP-53 (Mirny), only 32 were produced starting. 18 outputs carried on the train and transport resource test, during which the railways of the country covered over 400,000 kilometers. Tests were conducted in different climatic zones from Salekhard in the north to the south Chardjou from Cherepovets in the west to the east of Chita.

    In 1988

    . the Semipalatinsk test site were successfully conducted special tests BZHRK the effect for electromagnetic radiation ("Shine") and lightning ("Storm"). In 1991. on the NIIP-53 test was conducted on the impact of the shock wave ("Shift"). Tested two launchers and command post. Test objects were located one (PU loaded with her elektromaketom missiles, and KP) - a distance of 850m from the center of the explosion, the other (the second PU) - at a distance of 450m to the center of the end face of the explosion. The shock wave from a TNT equivalent 1000t does not affect the performance of the rocket and PU.

    first missile regiment with rocket PT 23UTTH stood on alert October 20, 1987 (Kostroma, commander V. Yu Spiridonov). By mid-1988 was deployed 6-7 regiments (about 20 PU, all near Kostroma). By 1999, three deployed missile divisions armed ICBMs and BZHRK PT 23UTTH (in Kostroma, pos. Starship under Perm and pos. Pine in the Krasnoyarsk Territory), each of which four missile regiment. Lineups are spaced about four kilometers from each other in fixed installations. When taking over the alert compositions become spread (see photo).

    when driving on country's rail network BZHRK capability to quickly change the deployment starting position up to 1000 kilometers per day.


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