All About R-36M2 / RS-20V Voivod - SS-18 mod.5-6 SATAN

[Major Shaitan Singh]

Maxim Pashnev (Obninsk), 2012 Intercontinental ballistic missile fourth generation. Complex and missile developed in the design office "South" (Dnepropetrovsk, Ukraine) under the leadership of the USSR Academy V.F.Utkina in accordance with the tactical and technical requirements of the Ministry of Defense and the Resolution of the Central Committee of the CPSU and the USSR Council of Ministers № 769-248 from 09.08.1983, the chief designer - S.I.Us and V.L.Kataev. V.L.Kataeva after transfer to the CPSU Central Committee replaced V.V.Koshik. Complex "Voivod" is created by the project of improving multilateral complex strategic heavy P-36M-UTTKh / 15P018 with 15A18 ICBM heavy class and is designed to defeat all kinds of targets protected by modern means of defense, in all conditions of combat use, in Vol. h. with repeated exposure to nuclear positioning area (guaranteed retaliation). In June 1979, "Southern" was developed a technical proposal for missile complex "Leader" with a heavy liquid ICBM fourth generation under the symbol 15A17. Draft project DBK R-36M2 "Voivod" (IDB index was changed to 15A18M to ensure compliance with the requirements of the SALT-2) was developed in June 1982.

Start of regular R-36M2. Probably one of the triggers for an extension of the warranty period of storage. (File photo by Radiant,http://russianarms.mybb.ru ).

When creating complex enterprise cooperation was as follows:
ON Southern Machine-Building Plant (Dnepropetrovsk) - production of missiles,
ON "Vanguard" - izgotovitlenie transport and launch container;
CB electrical instrument - the development of missile control system;
NGO "Rotor" - to develop a set of command devices;
KB factory "Arsenal" - aiming to develop a system;
CB "Energomash" - the development of the first stage of the rocket engine;
CB Khimavtomatika - development of the second stage of the rocket engine;
LACA - development of combat launch complex;
TSKBTM - development of the command post;
GOKB "Spotlight" - development of the system power supply;
NGO "Impulse" - to develop a system of remote control and monitoring
KBTHM - development of refueling system.
Monitoring the implementation of tactical and technical requirements of the Ministry of Defense of the USSR by the military representative of the Customer. flight tests complex with R-36M2 began at the site Baikonur ( NIIP-5) March 21, 1986 The first launch of a new ICBM (rocket 1L) of the silo OS on the site number 101 fails - after the release of the ICBM silo failed command tank pressurization of the first stage main engine does not start, IDB has fallen back explosion completely destroyed the mine.

Frames starting sample 15A18M 1L / R-36M2 (strategic missile systems of land-based. M., "Voennyy Parade," 2007).

Further flight tests were carried out in stages by type of combat equipment:
1. with a multiple warhead equipped with unguided warheads;
2. with unmanageable single warhead ("easy" BB);
3. with the original multiple reentry warhead mixed configuration (managed and unmanaged warheads). Chairman of the State Commission for the flight test was Deputy Commander of the Strategic Missile Forces, Colonel-General Yu.A.Yashin, deputy chairman, technical manager of tests - V.F.Utkin, and its Vice - V.V.Grachev and S.I.Us. High combat and operational characteristics of ground-based missile system confirmed (including physical experiments) and flight tests. Under the joint program of flight tests on the NIIP-5 were 26 starts, 20 of them successful. Reasons for unsuccessful launches installed. Carried out circuit-design improvements, will eliminate the identified deficiencies and complete the flight test 11 successful launches. Total (as of January 2012) conducted 36 launches, the actual missile flight reliability jointly carried out by the end of 1991 33 starts is 0.974. Develop a set of tools to overcome missile defense (BMD PCB) for the version with MIRV 15F173 was completed in July 1987 and for the version with "easy" one-piece MS 15F175 - in April 1988 flight tests with MIRV 15F173 completed in March 1988 (17 starts, 6 of them failed). Missile test with MS 15F175 began in April 1988 and was completed in September 1989 (6 starts, all successfully, as a result of which it was decided to reduce the mandatory program starts with 8 to 6). launch of R-36M2 (C) http : //militaryrussia.ru using data http://astronautix.com :

The first ICBM R-36M2 as part of a missile regiment embarked on experimental combat duty July 30, 1988 (The 13th Red Banner Missile Division, the garrison "Clear", p. Dombarovsky, Orenburg region, Russian Federation), in December of that year, said missile regiment atonement for combat duty in its entirety. Resolution of the Central Committee of the CPSU and the USSR Council of Ministers № 1002-196 from 08.11.1988, the missile system with MIRV 15F173 accepted for service. Missile system with MS 15F175 Resolution of the CPSU Central Committee and USSR Council of Ministers adopted for August 23, 1990 By 1990, two more were deployed ICBMs shelf with R-36M2.

Until the end of 1990 complexes were also put on combat duty in the division stationed at cities Derzhavinsk (1989, 38th Missile Division, UAH. "Steppenwolf", the Derzhavinsk, Turgay region, Kazakh SSR) and Uzhur (1990 city, 62nd Red Banner Missile Division, UAH. "Sunny" was Uzhur, Krasnoyarsk, Russian Federation). By the time of the collapse of the Soviet Union, despite the political and economic difficulties in the country, of operating units went quite rapidly - by the end of 1991 on the alert for a variety of information was supplied 82 ICBM R-36M2 (27% of the total number of heavy ICBMs USSR): - 30 Dombarovsky (47% of the IDB Division) - 28 Uzhur (44% of the IDB Division) - 24 Derzhavinsk (46% of the IDB division). In 1991, was designed by Yuzhnoye SDO preliminary design of heavy DBK fifth generation of the R-36M3 "Icarus", but the signing of the START-1 and the subsequent collapse of the USSR stopped its further development. In the preparation of the START-1 American side drew particular attention to the reduction of the complexes with the IDB and 15A18M 15A18, because, according to the Americans, these missiles could form the basis of pre-emptive strike forces from the Soviet Union (heavy ICBMs is 22% the number of ICBMs SMF while their combat equipment was more than 53% of all throw-weight of ICBMs RVSN).

The American side, taking advantage of the political and economic difficulties in the USSR and in fact defeatist stance country's top leadership in the negotiations, was able to insist on substantial quantitative reduction of these complexes - 50%. After the signing of the START-1 Treaty and the subsequent few months later collapse of the USSR production and deployment of missiles R-36M2 replace R-36M UTTKh has been suspended due to political and economic reasons (according to some reports, the latest missiles were produced in 1992). In 1996, year, according to the letter of international instruments aimed at reducing and non-proliferation of nuclear weapons and their delivery, all ICBMs position areas in the former Kazakh SSR (now the Republic of Kazakhstan) were removed from combat duty and then transported by special transport for disposal in Russia, those from the GMD missile division stationed near Derzhavinsk.

After the collapse of the Soviet Union mine missiles R-36M2, located on the territory of Russia, remained in operation and became part of the Strategic Missile Forces of the Russian Federation. Yuzhnoye SDO, as the leading developer of missile exercises supervision over their operation throughout their life cycle. As of the year 1998 in the Strategic Missile Forces of the Russian Federation were deployed 58 missiles R-36M2. By January 2012, two position areas (13th Krasnoznamennaya Orenburg missile division, but the "Clear", the Dombarovsky, Orenburg region, the 62nd Red Banner Missile Division, but the "Sunny" was Uzhur, Krasnoyarsk region) have been deployed R-36M2 in the version with MIRV, which is planned to keep on alert before the start of the 2020s. To date (2010) by continuous long-term work of cooperation between Russian and Ukrainian enterprises and research institutes lifetime warranty extended complex - December 2009 to 23 years instead of the original 15.

An important step to validate the basic performance characteristics of missiles are carried out launches of ICBMs R-36M2 of GMD in the Orenburg region, which began in 2004.To start the selected missile with a maximum service life. As of January 2012, held 3 starts, all - successfully. Regarding the number of deployed ICBMs R-36M2 "Voivod" we can assume that by the beginning of 2012, the Strategic Missile Forces of the Russian Federation were deployed ICBMs 55 of this type - 28 in the 62nd Missile Division (of Uzhur) and 27 in the 13th Missile Division (Mr. . Dombarovsky).Considering The ongoing combat training launches of ICBMs and work to extend the warranty period missiles under the ROC "charge", it can be assumed that the IDB 15A18M remain on duty until 2020 and possibly somewhat further in an amount of about 50 pieces.

In order to ensure a new level of performance characteristics and high combat effectiveness in the particularly difficult conditions of combat employment of the development of missile complex "Voivod" was conducted in the following areas: 1. Increase vitality silos and KP; 2.Ensuring the sustainability of command and control in all conditions of application of Kazakhstan; 3. Expanding operational capabilities to retargeting of missiles, including shooting unplanned target indications; 4. Ensuring the stability of missiles and warheads (BB application of the second level of resistance) in flight to damaging factors of land and high-altitude nuclear explosions; 5. Increase the autonomy of the complex; 6. The increase in the warranty period. 7. Bringing shooting accuracy to a level comparable with similar characteristics to the American ICBMs.

Efficiency, flexibility and efficiency of combat employment of the complex significantly increased due to (as compared to ICBMs 15A18): 1. Improve shooting accuracy by 1.3 times, which allowed for the first time to enter the accuracy comparable to the accuracy of shooting US ICBM; 2. Applications charges MIRV significantly increased capacity; 3. Increase the area of breeding zone of combat units (including in the area of arbitrary shape) is 2.3 times; 4. The operational start-up and retargeting on any unplanned target designation transmitted from senior management. SU implemented the world's first direct methods of guidance, providing the ability to calculate the task in flight ( US ICBM this complex do not have the opportunity until now ); 5. Increase 3 times longer battery industry; 6. 2-fold reduction of time combat readiness through a continuously operated throughout the alerting complex command devices (PAC).

One of the main advantages of the missile system with R-36M2 is the possibility of missile launches in a retaliatory strike under the influence of land and high-altitude nuclear explosions the starting position. This is achieved by increasing the survivability of the missile in the silo, and a significant increase in resistance to missile effects of a nuclear explosion in flight. The housing is made with materials of increased strength. The outer coating is made over the entire length multifunctional missile (including nosecone) for protection against the damaging effects. Missile control system as well adapted to the passage when starting the footprint of a nuclear explosion.Engines I and II rocket stages boosted by traction, enhanced stability of all the major systems and components of the missile system.

As a result, the radius of the affected area rocket blocking nuclear explosion compared with a rocket 15A18, reduced 20-fold resistance to X-rays is increased by 10 times, the gamma-neutron radiation in a ~ 100-fold. Provided resistance to the effects of the rocket dust formations and large soil particles present in the cloud at ground nuclear explosion. Realized for launch on start-up levels of resistance to missile PFYAV ensure a successful launch it after the explosion unaffected directly by PU and without reducing alertness when exposed to neighboring PU. Time delay start to normalize the situation after the nuclear explosion unaffected directly by PU - no more than 2.5-3 minutes. So, high performance rocket 15A18M to ensure a higher level of resistance to PFYAV were achieved by: - use of a protective coating of the new development, applied to the outer surface missile body and provides comprehensive protection against PFYAV; - application of the SU, developed on the basis of the element with high durability and reliability; - marked on the sealed instrument compartment, which housed the equipment SU, special coating with a high content of rare earth elements; - the use of screening and special methods of placing missiles onboard cable network; - the introduction of special software maneuver missiles while passing clouds ground nuclear explosion.

Design work to ensure the stability of the new rocket to land YaV PF based on the new refined mathematical model of this kind of nuclear explosion, specially developed by experts TSNIKI-12 which contributed to the successful solution of tasks to ensure the stability created while the fourth-generation missiles. Considering the need for a given high-level resistance missiles "Southern" and other development organizations, with the active participation of the Research Institute of the industry and the customer, a large body of theoretical and experimental work to establish and validate the specified requirements. Stand-alone test case design elements, assemblies and systems were carried out on experimental bases Yuzhnoye SDO, NGO "Hartron" and other related organizations. On modeling devices were tested on the impact of ionizing radiation, X-rays, the effects of electromagnetic pulse, to the shock effect of large soil particles on the mechanical and thermal effect of air shock waves and soft X-ray light emission.

Were organized and conducted comprehensive tests at the Semipalatinsk test site USSR Ministry of Defense, including: large-scale trials with a rocket launcher on the effects of seismic waves of nuclear explosions (physical experiments "Argon") and the effects of electromagnetic pulse;testing of various components and systems missiles, including operating system management and sustainer stages, the effects of ionizing radiation and hard X-ray spectrum, etc. After the first test launches at Baikonur rocket range in the United States received the designation TT-09 (Tyura-Tam - Baikonur, 9-1 unidentified object) and for some time was designated as SS-X-26. The launcher and basing : implemented for launch on start-up levels of resistance missiles PFYAV to ensure a successful launch it after the explosion unaffected directly by PU and without reduction alert when exposed to neighboring PU. Time delay start to normalize the situation after the nuclear explosion unaffected directly by PU - no more than 2.5-3 minutes. Development of the launch complex was based on the launch complex 15P018. At the same time maximize the use of existing engineering structures, communications and systems.

Designed silos 15P718M ultrahigh protection from PFYAV by conversion silo missile systems 15A14 and 15A18. Modified launch complex is guaranteed to withstand excessive pressure in the shock front of a nuclear explosion the size of more than 100 atmospheres. During the development and testing of complex "Leader" under the leadership of KBM (Kolomna) N.I.Guschina was a complex of active protection silos Strategic Missile Forces of nuclear warheads and high-precision conventional weapons (probably OCD "Mozyr" ), and for the first time in the country carried out low-altitude high-speed non-nuclear intercept ballistic targets. The complex includes: - 6 or 10 single automated PU surface mine laying, providing high protection against PFYAV, with complex, including fortification, protection of conventional ammunition, including precision-guided weapons, defined in PU missiles in TPK and radio antennas ravnozhivuchimi command and control ; - fixed mine KP, located near one of the PU, which provides high protection against PFYAV, with complex, including fortification, protection of conventional ammunition, including precision-guided weapons; - means SBU and communication - internal power supply system and protection; - registration system YaV ; - mezhploschadnaya cable connection, roads and communications.

Open the lid silos 15P718M R-36M2 ( http://vpk-news.ru ).

BSP on PU and PD CP provides the possibility of placing elements of the complex means of protection against conventional munitions medium and large caliber, as well as active protection from BB in nuclear design. Operating System RK - centralized in scale missile division based on class regulatory scheme operation and preventive missiles regulated by volume, maintenance of combat equipment, which combined maintenance systems PU. During operation, provided:
- replacement warheads;
- transportation and rocket warhead isothermal units;
- Ros overload units and missiles in TPK;
- two kinds of alert SU: increased and sustained;
- remote periodic inspection and calibration of the PAC, the definition of the basic directions translation SU from one another in readiness.In the process of developing a set of successfully taken steps to further improve the survivability UKP 15V155 for DBK 15P018, which resulted in an improved UKP for DBK 15P018M.

MSE 15P718M with TPK R-36M2 (Called time. Rockets and spacecraft design office "South". Edited by S.N.Konyuhova. Dnepropetrovsk, Art Press, 2004). Monument - TPK R-36M2 / 15A18M. Orenburg, 21.05.2010 (photo - Zmey Kaa Kobra, http://ru.wikipedia.org ). Set with RIC 15A18M / R-36M2 in mine PU ( http: //www.uzhur-city. RU ).

Rocket R-36M2 / 15A18M :
Design - airframe has Wafer-welded aluminum-magnesium alloy high-strength cold-worked AMg-6. The outer cover (MFP - multifunction coating) holds the entire length of the multifunctional missiles (including fairing) to protect against the damaging effects. Given the need to pass through pylegruntovye education explosion - mushroom clouds of ground particles of different size, hovering in the vortices at an altitude of 10-20 km above the ground, the rocket was performed with no protruding parts. The missile was developed in size and weight of the starting rocket 15A18 two-stage scheme with a serial arrangement stages and elements of breeding warheads. The rocket launch saved scheme, stage separation, separating warhead, breeding elements of combat equipment, which showed a high level of technical perfection and reliability as part of the missile 15A18. The missile is located in TPK 15YA184 made of organic materials (high brand fiberglass). Complete assembly of the rocket, docking it with the systems on the TPC, and verification are made at the factory.

TPK is equipped with a passive system maintain moisture conditions when the missiles it in PU. Case production TPK for 15A18M was requested by "Vanguard" (Safonovo Smolensk Oblast, RSFSR), the development of documentation on special machines, stacks, tools and other non-standard equipment produced UkrNIITmash, unique manufacturing process equipment entrusted to Southern Engineering Plant. To accompany the CD and development processes in the software, "Vanguard" was organized by the Special Design and Technology Bureau. Rocket from the date of manufacture in the factory throughout the life cycle is in TPK. Pads for "mortar" start of the WPK with progressive and stable characteristics allow to obtain optimal regimes of the rocket at the start of the WPK and the initial phase. In this case, the law of the requested change of gas pressure in the space provided podraketnom monobloc charges with progressiruemoy burning surface and the scheme of the few consistently working pads. Pads developed jointly by Yuzhnoye SDO and CLRI "Union" (fuel charges, under the leadership of BP Zhukov, Lyubertsy, Moscow region, Russian Federation).

15A18M without the warhead and missile TPK also without MS (Weapons of Russia. Weapons and military equipment SRF. M., "Military Parade", 1997).

 

[Major Shaitan Singh]

Rocket 1L and a few were made in the following form "6000.00." This variant is characterized by a large volume of telemetry equipment.Two additional cable trays for telemetry were routed through I and II march and battle stages and one additional cable trough for telemetry was sandwiched between II and military marching steps. At the bottom end of combat step has an extra bar with folding antennas.Outside on the body combat stage were two boxes with antennas. Of the 14 seats MS combat-capable units with a set of telemetry equipment is 8, and the remaining 6 - conical cassettes with telemetry equipment. Tanks rocket stages 1L and 2L were not covered by the MFP because of the complexity of the process for applying MFP tanks that had not been worked out before the end of the time of manufacture of the first flight of missiles to begin flight tests.

Rocket R-36M2 (Called time. Rockets and spacecraft design office "South". Edited by S.N.Konyuhova. Dnepropetrovsk, Art Press, 2004)

Control and guidance - the rocket launched algorithmic scheme-protection equipment management system of gamma radiation from a nuclear explosion - when entering the zone of influence of nuclear explosion sensors shut off control system, and immediately after leaving the zone SU turns on and displays the desired trajectory of the missile. Use specially designed equipment element base increased resistance to the effects of a nuclear explosion, 2 times improved performance of the executive bodies of the automaton stabilization control system, fairing separation is carried out after leaving the area of high-rise block of nuclear explosions.

The control system autonomous inertial - developed in KB "Hartron" and Produced by the NGO "Hartron" (NGOs electrical instrument) (Chief Designer V.G.Sergeev, chief designer on the topic - Perederiy AI) based on two high CEC (airborne and ground-15L860 15N1838-02) new generation and continuously working in while patrolling high-precision systems (onboard and ground-15L861 15N1838 "Atlas") command devices with float sensor elements to develop SRI PM (Chief Designer V. Kuznetsov).

To improve reliability, CEC all the basic elements are redundant.In the process of alerting ODCC provides communication with ground units. SU for the first time in the world sells direct methods of guidance, providing the ability to calculate the task in flight. In order to maintain the required temperature continuously operating devices, a special thermal control system equipment SU, which had no analogues in the domestic rocket (clear heat in the amount of PU). In this case, the system had to create a "no margin for error" - due to tight deadlines PAGE worked out on the rocket during flight tests.

The successful operation of the system confirmed the correctness of the principal decision in the development of PP and its design lifetime.New powerful ODCC made using semiconductor "burn through" permanent operational and electronic storage devices. The main element base develops and produces in "Integral" (Minsk, BelSSR) and provide the necessary level of radiation resistance. Also the building blocks of the first bead complex included in the USSR implemented dedicated memory block of ferrite cores with an internal diameter of 0.4 mm, which is pierced through the 3-wire diameter smaller than a human hair. For one of the types of warheads 15A18M was developed for the first time in the Soviet Union passed flight tests of a memory on cylindrical magnetic domains. Creating a missile system with 15A18M took place in a very short time. For the control system it was upgrading from a previous missile system, but it required the design of totally new devices, including ODCC.

Relatively little known fact is that by the beginning of 1987 there was a need major changes to control systems in connection with the need to go to the basic elements of higher quality. IDB 15A18M while already undergoing flight tests. A series of spring and summer meetings of ministers, commanders SMF managers developed by the industry and resulted in the decision to release the forcing of the new control system with manufacturing and perfecting them at two enterprises: the pilot plant of the NGO "Hartron" and by "Kiev Radio". To coordinate set up a special operational-technical group. In late September 1987 the group started to work. The work was seven days a week, with the most minimal formalism. By the end of 1987 at the NGO "Pivdenmash" complete sets of new equipment. All required tests were passed on time. Aiming missiles in azimuth is provided by a fully autonomous system (without the use of ground-based geodetic network), the system uses an automatic gyro aiming to razarretirovannom position, proactive system startup and quantum optical gyro with a high speed, allowing to perform multiple correction of sight for given models YaV on PU.

Components of the system aiming placed in PU. 15SH64 sighting system provides the primary definition of the azimuth direction when setting the base missiles on alert and storing it in the process of alerting, including the nuclear impact on PU, and restore basic azimuth direction after exposure. Engines : rocket introduced the most advanced for its time technical solutions - improved engine performance, the introduction of the optimal scheme off control, execution control stage II in the "flush" option in the cavity of fuel, improved aerodynamic performance. As a result, energy capabilities 15A18M increased by 12% compared with a rocket 15A18 when all conditions limit the starting size and weight imposed by the SALT-2 Treaty.

Missiles of this type are the most powerful of all the world's intercontinental missiles. In order to reduce the exposure time PFYAV, as well as to reduce the probability of detection of missile defense systems both stages boosted engines. The structure of control 15D285 (RD-274), the first stage unit 15S171 rocket consists of four independent single-chamber LRE 15D286 (RD-273) with turbopump fuel supply system, a closed circuit formed by the oxidizing afterburning gas gasification and pivotally mounted on the frame of the tail section of the first stage. Deviation engines Command control system provides control rocket flight. Developer engine - KBEM (Chief Designer V.P.Radovsky). The proposal to upgrade the engines for the R-36M2, providing a boost traction and improved resistance to PFYAV, was received by the CB "Energomash" in 1980. Technical proposal for the development of the RD-263F was published in December 1980. In March 1982, released preliminary design for the development of modernized first-stage engine RD-274 (4 motor unit RD-273). Assumed to increase the pressure in the combustion chamber gases up to 230 atm, increase speed to TSA 22500 rev / min.

As a result of improvements increased engine thrust to 144 ton, specific impulse at the Earth's surface has increased to 296 kg · s / kg. Developmental testing were completed in May 1985. Serial production of engines were deployed at "Pivdenmash." To block 15S172 second stage of the rocket, control, developed in 1983-1987., consists of two engine united in a motor unit RD-0255: the main sustainer engine RD-0256 and RD steering -0257, both - development KBKhA (Chief Designer AD Konopatov). Development of engines made in 1983-1987 gg ( source ). Main engine, single chamber, with turbopump components supply is made in a closed circuit with afterburning oxidative gasification gas. Main engine is located in the fuel tank, thereby increasing the density of filling volume rocket fuel (MDBs such a decision was taken for the first time, before such construction scheme was used only for SLBMs). Steering motor - with four-rotating combustion chambers and a TNA, made in a closed circuit with afterburning oxidative gasification gas.

Engines of all levels work on high-boiling liquid stable dolgohranimyh propellants (UDMH + AT) and fully ampulizirovany. In the fluid circuit (ASG) of the rocket as previous representatives of this family, has implemented a number of critical decisions, will significantly simplify the design and scheme of the CBC, to reduce the number of elements of automation, eliminating the need for preventive work with the CBC and increase reliability while reducing weight. CBC features are complete rocket systems ampulizatsiya fuel rocket after refueling with a periodic control the pressure in the tanks and the elimination of compressed gas from the board of the rocket.

This will gradually increase the time spent in the Republic of Kazakhstan on full alert to 23 years with the potential for exploitation of up to 25 years or more. For preliminary pressurization tanks traditionally used chemical boost circuit - by injection of the main components of the liquid fuel on the mirror in the tanks. As for ICBMs 15A18, implemented the "hot" oxidizer tank pressurization (T = 450 ± 50 ° C) and "superhot" boost fuel tanks (T = 850 ± 50 ° C) with a ratio control components gasifiers. Separation of the 1st and 2nd stages - Cold gas dynamic circuit permits operation of explosive bolts, opening special windows - nozzles gazoreaktivnoy braking system and the expiration of gases through them the boost fuel tanks. 15S173 combat stage, in which the basic equipment management system and propulsion system ensuring consistent sighting breeding ten big blinds, unlike missiles 15A18 functionally part of the rocket and joined with the second stage of explosive bolts. This allowed for a complete build a rocket in a factory, to simplify the technology works on the battle sites, to increase the reliability and safety of operation. Managing four-LRE 15D300 (RD-869) combat stage (design bureau Yuzhnoye SDO-4) is similar to the design of the scheme and its prototype - for the rocket engine 15D117 15A18. In the process of working out a few engine improved its expenditure, traction performance and increased reliability.Separation of military and 2nd stages - Cold gas dynamic circuit permits operation of explosive bolts, opening special windows - nozzles gazoreaktivnoy braking system and the expiration of gases through them the boost fuel tanks.

In April 1988, production of breeding stage rocket was transferred to the enterprises of the RSFSR. To launch, a new one-piece nose fairing ogival shape provides an improved aerodynamic performance and reliable protection from damaging factors warhead nuclear effects, including the formation of dust and large particles of soil. Fairing separated after passing coverage of high-rise block of nuclear explosions. Branch fairing produced by placing in front of the fairing sliding block with dual-mode solid propellant compartment. Features Control: Oxidizer - nitrogen tetroxide Fuel - floppyTraction control (on the ground / in a vacuum), ts: - I stage of 468.6 / 504.9 - stage II - / 85.3 - stage dilution - / 1.9 Specific impulse control (on the ground / in a vacuum), with: - I stage of 295.8 / 318.7 - II stage - / 326.5 - stage dilution - / 293.1

Propulsion RD-0255 the second stage of the rocket 15A18M ( Отечественная военная техника (после 1945 г.) • Главная страница ).

TTX missiles :
Length - 34.3 m
diameter - 3 m Mass start: - with MIRV 15F173 - 211.4 m - with MS "light" class 15F175 - 211.1 Weight of warhead: - with MIRV 15F173 - 8.73 m - with MS "light" Class 15F175 - 8.47 m Weight of fuel: - I stage - 150.2 m - II level - 37.6 m - stage dilution - 2.1 m ratio energovesovogo perfection Gpg / Go - 42.1 kg / ton Range Maximum: - with MIRV 15F173 (10 BB capacity 0.8 Mt) and IRT PRO - 11,000 km - with "easy" one-piece MS 15F175 capacity of 8.3 Mt and IRT PRO - 16000 km CWE - 220 m flight reliability (end of 1991) - 0.974 generalized reliability index - 0.935 Resistance to PFYAV missiles in flight - II level (provided retaliatory start) Warranty Period Spent on duty (on bezreglamentnoy scheme for PU) - 15 years warranty period extended from 10 to 25 years in service in combat duty rocket is in full combat readiness in the silo.

Combat use is possible in any weather conditions at temperatures from -50 to + 50 ° C and wind speed at the surface to 25 m / s, up to and in the nuclear impact on BRC. warhead types : TTT included new missile warheads four types of headaches parts of the upper-level resistance to PFYAV: 1. monoblock MS 15F171 with "heavy" (capacity of at least 20 Mt) BB 15F172; 2. MIRV 15F173 with ten high-speed unmanageable BB 15F174 high power class at least 0.8 Mt each; 3. monoblock MS 15F175 with "easy" (capacity of at least 8.3 Mt) BB 15F176; 4. MIRV 15F177 mixed configuration of six unmanaged (capacity of at least 0.8 Mt) BB 15F174 and four managed (capacity of at least 0.15 Mt) BB 15F178 with active radar homing system on digital maps. 5. Managed combat unit 15F178 new generation to create a normal variant to equip missiles 15A18M, designed for HSR 15F177 mixed configuration. Preliminary design of UBB was completed in 1984. The control block is shaped biconical body minimum aerodynamic drag. As executive bodies on the atmospheric flight UBB site were taken tiltable conical stabilizer - for pitch and yaw and roll aerodynamic control surfaces. In flight, provides a stable position of the center of pressure unit with changes in the angle of attack. Orientation and stabilization of UBB is atmosphere provides jet thrust power plant with liquefied carbon dioxide. To develop the control system were brought NGOs "Electrical Appliance" as the main developer, as well as NGOs and NGOs TP AP.

Developer team gyroscopic instruments is an NGO "Rotor". During the work on staffing UBB was established research unit option to confirm the aerodynamic characteristics of starts by the inner track "Kapustin Yar - Balkhash". In the period from 1984 to 1987. there were four starting research BB, all with positive results. The achieved accuracy was not more than 0.13 km quo. Blocks for the first launches were made at PO UMZ, and further production in July 1987 was transferred to the enterprise of the RSFSR (head - Orenburg Engineering Works). Thermonuclear charge 15F179 small class power UBB staff should have a capacity of not less than 0.15 Mt at 0.08 km shooting accuracy quo. The first launch of UBB 15F178 was held January 9, 1990 in unmanaged mode for the internal circuit. Subsequent flight tests UBB held in a controlled manner. There were three start on the inside track and three launches missiles as part 15A18M. The results prove the reality of creation starts UBB and equipping them 15A18M. To continue the flight tests were prepared by two missiles 15A18M two carriers 8K65M-P and a full set of warheads. However, after the collapse of the USSR in 1991, work on the UBB were closed.

For warheads created DBK were used deep modification of the exhaust and proven thermonuclear weapons development VNIIEF (Arzamas-16, RSFSR), tested in the 1970s. The developed products are characterized by: a high degree of operational reliability and trajectory; almost absolute nuclear safety; high fire - and explosion during the entire life cycle (including in case of emergency); high resistance to the effects of a nuclear explosion; ensuring high combat effectiveness in the defeat of the target. For options with MIRV warheads 15F173 and 15F177 MS performed on the two-tier scheme. For all types of combat equipment used advanced momentumless separation device BB. Twist all types of warheads warheads by using pyrotechnic devices. For use in the warheads designed to overcome missile defense system highly ("kvazityazhelye" and "light" decoys, chaff, jamming generators and so on.), which are placed in special tapes, mounted on 4 seats of MS (multiple warheads for 15F173, the remaining 10 seats are engaged BB 15F174). Ejection of decoys of cassettes used solid charges. Also applied radio-insulating covers BB. Special techniques are used at a dilution of BB and orientation, complicating enemy miscalculation breeding scheme warheads.

Originally PCB PRO was made at "Pivdenmash", but with the May 1986 production was transferred to the associated companies of the RSFSR. In the process of SSI was decided to exclude from the compulsory composition of combat equipment "heavy" and BB HSR mixed configuration. MS with "heavy" BB is ready for production, but has not been flight testing (on a number of data to meet the requirements of the SALT-2). Modifications : Status : USSR / Russia - 1996 August-September - from silos in Derzhivinske ( Kazakhstan) exported to Russia last R-36M2. - 2009 - with the words of the commander of the Strategic Missile Forces Lieutenant General Andrew Shvaychenko of RS-20B (probably meant it 36MUTTH P): "Recent missiles of this type in 2009 decommissioned SRF and used for eradication program by starting with a fair breeding spacecraft ("Dnepr"). T.ena Strategic Missile Forces were only ICBM R-36M2 ( ist. - strategic nuclear weapons). - 2010 December 20 - the commander of the Strategic Missile Forces in the media General Sergei Karakayev said that the life of R-36M2 extended until 2026 - 2012 October 11 - The media report that the term hkspluatatsii ICBM RS-20V will be extended to 30 years, ie, missiles will be on duty until 2020 - 2014 June 19 - media quoted a representative of "Southern" (Dnepropetrovsk, Ukraine) reported that "Southern" continues to service ICBM R-36M2 despite the cooling of relations between Ukraine and Russia, "as pointed out by the" Southern ", the termination of cooperation with Russia is possible only in the case of the corresponding decree of the President of Ukraine, which is not yet released." According to the agreement between the "Southern" and the Ministry of Defense of Russia ICBM maintenance should be carried out until 2017 ( source ).Deploying ICBM R-36M2 (C) http://militaryrussia.ru :