Strategic Missile Forces: Strategic Missile Forces

History of the Strategic Missile Forces

Forwarding is the case. In the history of RV:

1946 – 1959 – Assigned to the field of military operations.

From 1959 to 1965, it was a military-geographical area. and in any theaters of military operations.

In 1962, during which the RSD R-12 and R-14 were secretly deployed.

1965 – 1973 – he was in the United States of America. contribution to the military-strategic equilibrium between the USSR and the USA.

1973 – 1985 –––––––––––––––––––––––––––––––––––

1985–1992 – 4th generation, liquidation in 1988–1991. medium-range missiles.

Since 1992, it has been the case of the United Kingdom. Mobile phone systems for mobile and stationary mobile 5-generation.

It has been a great deal of effort. In accordance with 13/5/1946 1017-419 Issues of reactive legislation, it was determined.

The State Central Firing Range (Kapustin Yar), GAU. Brigade of RVGK (commander – Major General of Artillery A.F. Tveretsky). In December 1950, it was formed, in 1951-1955. – 5 more compounds, which received a new name (since 1953), – RVGK engineering teams. Until 1955, they were equipped with warheads (general designer S. P. Korolev). By 1958, the brigades had more than 150 combat training launches of missiles. In 1946 – 1954, they were part of the artillery of the RVGK and they were part of the artillery of the Soviet Army. The headquarters of the Soviet Army. In March 1955, MI Nedelin’s report was created.

It was determined by the brigades command.

For the first time in the world. Mankind – This is the era of practical cosmonautics.

In the 2nd half of the 50s. R-5 and R-12 Formations of Nuclear Reactors (KG Spanner) and MK Yangel, with 1,200 km and 2,000 km of ICBM P-7 and R-7A (General Designer S. Korolev). In 1958, the RVGK, armed with the operational R-11M and R-11M, were transferred to the Ground Forces. Angara (commander – Colonel MG Grigoryev) ICBMs.

For example, a new type of aircraft is required. In accordance with the Decree 1384-615 of December 17, 1959, the aircraft was created as an independent aircraft. Decree of the Russian Federation 1239 of December 10, 1995, the Day of the Strategic Missile Forces.

There were some directorates that were formed in the United States of America. and services. Forwarding of Air Forces, United States of America, Forces and Armed Forces, missile weapons, bases and warehouses of special weapons. The Strategic Missile Forces also included the 4th State Central Test Site (Kapustin Yar); 5th Research Test Site MO (Baikonur); separate scientific testing station in the village. Keys on Kamchatka; 4th Scientific Research Institute of the Moscow Region (Bolshevo, Moscow Region). In 1963, on the basis of the Angara facility, the 53rd Research Institute was established.

06/22/1960. Forms of M.I. Nedelin (chairman), V.A. Bolyatko, PI Efimov, M.A. Nikolsky, A.I. Semenov, V.F. Tolubko, F.P. Thin, M.I. Ponomarev. In 1960, the Forces was enacted. In the case of the command and control systems, troops and combat vehicles were introduced.

In 1960 – 1961 on the basis of long-range air armies, rocket armies were formed, which included RSD formations. The RVGKs were reorganized, they were reorganized and ICBMs were registered. The ICBM is the missile regiment. Until 1966, the intercontinental BRK R-16, R-9A were adopted (gen.constructors MK Yangel and SP Korolev). In the RSD, the troops were formed, R-12U, R-14U with the mine group (general designer MK Yangel). The first missile formations and units were staffed mainly by officers from the Navy, the Air Force and the Ground Forces. In the course of the training, she was

In 1965 – 1973, the P-36 radar systems, distributed over a large area (MK Yangel, VN Chelomei). In 1970, it was created. The second generation of the DBK has been provided for the rocket weapons.

In 1973 – 1985 BRK RS-16, RS-20A, RS-20B and RS-18 (Gen. Designers VF Utkin and VN Chelomei) (Gen. Designer AD Nadiradze), the BRK were. The missiles used remote control, providing remote re-targeting of missiles before launch.

In the years 1985 – 1992. The RS-20V mine-for-railings were rescued by the RS-20 minera-based (RS-20V). gen.constructors VF Utkin and AD Nadiradze). He has been on the line between autonomy.

For example, there has been a limitation of the number of nuclear forces. The RSD-10 (“Pioneer”) missiles – by launching from field combat positions in areas gg. Chita and Kansk.

In 1997, the United States Forces and the United States of America. Since June 2001, the Forces have been transformed.

For example, it’s important to follow up. This is a case of technical strategy.

The appointment of strategic missile forces

It is a strategic component of its strategic nuclear forces (RVSN). It has been noted that the enemy.

Stabilization and national security.

The system is characterized by a highly dynamic transformation of the system of international relations. After the end of the bipolar confrontation, a pair of countries or groups of countries emerged. It is often based on the law of civil law. Thus,

It’s not worth it. He was interested in maintaining international relations. However, it’s not a problem. The rule of law is that use force.

Today, Russia has sufficient military power. The Armed Forces envisages their development. However, it is not yet been completed. A number of states and general forces. There are no changes in the number of strategic nuclear forces in the country.

It is noteworthy that it’s not a matter of fact. a potential aggressor. It is the registrars of the national defense of the Russian Federation.

However, it is not a problem. Today, our strategic nuclear forces most closely correspond to the geostrategic and economic situation of the country. In particular, it is important. In addition, it’s possible that it’s not a problem.

Strategic Missile Forces are one of the three components of the SNF (along with naval and aviation SNFs). The United States of America has been responsible for its strategic component. Therefore, even today, about 2/3 of all the carriers and warheads of the SNF are concentrated in their combat composition. It is not only quantitative parameters, but also its inherent qualitative characteristics, such as: the influence of the enemy.

It has been noted. For all countries, it’s why we’ve been able to apply to ICBMs. ICCMs and their silos. The agreement on the START-3 Treaty and the START-1 Agreement and the START-2 Agreement.

From June 1 of this year. Forces are transformed into the central space. It is important to carry out their combat missions for nuclear deterrence. The infrastructure has been created for the radionuclide system. them.

It has been established that it has been developed for the period of 2005. combat and technical characteristics. This complex subsequently formed the group of the Strategic Missile Forces.

There are no plans for a reduction.

For those of you, we’ve given the following tasks:

  • At a minimum level of deterrence;
  • Forces in line with their missions.

The following are the key factors that have been taken for a group of participants.

  • First, the economic opportunities of the state. It is no secret that these opportunities are currently quite limited. It seems to be the case today;
  • Secondly, the fulfillment of contractual obligations. Forces have been taken to eliminate all PC-18s, i.e. go completely to the grouping of monoblock missiles;
  • Thirdly, the state of the military threats to Russia. If you’re not in the least, you can’t keep up with the situation. It can be solved by international political forces to 1,500 units. It would be a matter of course to take a long time.

Forces and location

Forces include the 27th Guards Rocket Army (headquartered in the city of Vladimir), the 31st Rocket Army (Orenburg), the 33rd Guards Rocket Army (Omsk). The 53rd Soviet Army (Chita) was disbanded at the end of 2002. It will also be disbanded over the next few years. As of July 2004, there are 15 missile armies, which are armed with combat missile systems. According to the Strategic Missile Forces in November 2004, the number of missile divisions will be reduced to 10-12.

There are six areas of intercontinental ballistic missiles: Kozelsk, Tatishchevo, Dombarovsky, Uzhur, Kartaly, UR-100UTTH missiles are on-line as well as the BRs: Yoshkar-Ola, Teikovo, Novosibirsk, Irkutsk, Barnaul, Nizhny Tagil, Vypolzovo, Drovyanaya. 12 launchers RS-22 “Scalpel” located in Kostroma, Krasnoyarsk and Perm.

Missile systems RVSN

As of July 2004, the RVSN was armed with 608 nuclear warheads:

Missile complex Capacity of one warhead, kt Amount of warheads Total power, kt Locations
R-36MUTTH / R-36M2 (SS-18) 108 ten 1080 Dombarovsky, Kartaly, Uzhur
UR-100NUTTH (SS-19) 130 6 780 Kozelsk, Tatishchevo
RT-23UTTH (SS-24) 15 ten 150 Kostroma
Poplar (SS-25) 315 one 315 Teykovo, Yoshkar-Ola, Yurya,
Nizhny Tagil, Novosibirsk,
Kansk, Irkutsk, Barnaul, Vypolzovo
Topol-M (SS-27) 40 one 40 Tatishchevo

Technical equipment RVSN

At the end of 2003, the Russian Army. According to Deputy Minister of Defense, Aleksey Moskovsky, for his current year.

“Iskander” is designed to strike at small small targets. Does not exceed 300 km. It has two missiles on the launcher, which significantly increases the firepower of the missile battalions and brigades. It is the nuclear weapons in terms of effectiveness. “Iskander” was developed in the engineering design bureau.

His model was demonstrated in the Nizhny Tagil in July 2000.

R-36MUTTH development (RS-20B and SS-18) and R-36M2 (RS-20V, SS-18) was done by the Yuzhnoye Design Bureau (Dnepropetrovsk, Ukraine). The R-36MUTTH missiles were carried out in 1979-1983, the R-36M2 missiles in 1988-1992. The R-36MUTTH and R-36M2 two-stage liquid missiles, can carry 10 warheads (there is also a one-piece version of the rocket). The Southern Machine-Building Plant (Dnepropetrovsk, Ukraine). Forts for all R-36M2 missiles (about 50 missiles) on combat duty. If you are up to 25-30 years old, you should be able to keep up with the service life.

The UR-100NUTTH (SS-19) missiles were developed by the NPO Mashinostroeniya (Reutov, Moscow Region). The deployment of missiles was carried out in 1979-1984. The UR-100NUTTH missile is a two-stage liquid, carrying 6 warheads. Production of missiles carried plant them. M. V. Khrunichev (Moscow). To date, part of the UR-100NUTTH missiles have been decommissioned. It can be preserved for several years. In addition, Russia acquired 30 UR-100NUTTH missiles from Ukraine that were in storage. It is planned that after 2030.

The RT-23UTTH missiles (SS-24) were developed at the Yuzhnoye Design Bureau (Dnepropetrovsk). Missile versions for the mine-based complex and the railway-based complex were created. The version of the complex was carried out in 1987-1991, the mine version in 1988-1989. The RT-23UTTH three-stage solid-fuel missile carries 10 warheads. Production of missiles carried Pavlograd Machine-Building Plant (Ukraine). It has been eliminated.

Topol ground-based missile systems (SS-25) were developed at the Moscow Institute of Thermal Engineering. Missiles were deployed in 1985-1992. The Topol three-stage complex solid-propellant missile carries one warhead. The production of missiles carried Votkinsky engineering plant. Up to date, it’s possible to complete the service life of the missiles.

Brief description of rockets

Pioneer 3

Pioneer-3 is a two-stage medium range ballistic missile system. The development of the complex was carried out by the Moscow Institute of Heat Engineering. Passed the test in 1986.

For the rocket, it has been developed for the warheads. The Minsk Automobile Plant has been developed for a comfortable and cozy cabins for personnel. The tests were interrupted during the mid-range and the shorter-range missiles. Mass production of missiles was not deployed.

R-36M. 15A14 (PC-20A) [SS-18. Satan]

R-36M – a two-stage intercontinental ballistic missile. It was equipped with a warhead and a warhead. Developed by Yuzhnoye Design Bureau under the direction of Mikhail Yangel and Vladimir Utkin. Development started on September 2, 1969. LCIs were conducted from 1972 to October 1975. September 25, 1974. Adopted on December 30, 1975.

Single-chamber engines RD-263 consisting of four engines. The engine was developed in KB Energomash under the direction of Valentina Glushko. The second stage of the engine design was developed by Alexander Konopatov. The components of fuel are UDMH and nitrogen tetroxide. ShPU OS developed in KBSM under the leadership of Vladimir Stepanov. Start method – mortar. The control system is autonomous, inertial. Developed in NII-692 under the leadership of Vladimir Sergeyev. The system was developed in the Central Scientific Research Institute. The combat stage is equipped with a solid-fuel propulsion system. The unified KP was developed at TsKB TM by the leadership of Nikolay Krivoshein and Boris Aksyutin.

Serial production of missiles deployed at the South Machine-Building Plant in 1974.

TTX rocket “Voivode” P-36M2. 15A18M
Maximum firing range with “light” monoblock warhead 16,000 km
The firing range of the rocket with a “heavy” warhead 11,200 km
Firing range missiles with MIRV IN 10,200 km
Maximum starting weight 211 t
Head mass 7.3 t
Rocket length 34 m
Maximum case diameter 3m
Mass of fuel 188 t
Traction propulsion engine first stage on the ground 400 tf
Thrust propulsion engine first stage in the void 450 tf
Specific impulse thrust sustainer engine first stage on the ground 293 kgf · s / kg
Specific impulse thrust sustainer engine first stage in a vacuum 312 kgf · s / kg
The first stage 200 atm
Internal diameter of the silo concrete shaft 5.9 m
Depth of the silo 39 m
Missile readiness 30 s

R-36M UTH. 15A18 (PC-20B) [SS-18. Satan]

R-36M UTTH – two-stage intercontinental ballistic missile. Developed in Yuzhnoye design under the direction of Vladimir Utkin. Equipped with a wringer with ten warheads. Development started August 16, 1976. LCIs were held at the Baikonur test site from October 31, 1977 to November 1979. Adopted on December 17, 1980.

Mass production of missiles deployed in Dnepropetrovsk.

  • The maximum firing range is 11,500 km.
  • The initial warranty period of storage is 10 years.

The characteristics of the R-36M UTTH rocket are P-36M.

“Voivode” P-36M2. 15A18M (PC-20B) [SS-18. Satan]

R-36M2 – two-stage intercontinental ballistic missile. Equipped with a multiple rocket launcher warheads and single-block warheads. Developed in Yuzhnoye design under the direction of Vladimir Utkin. The technical proposal was developed in June 1979. It was conducted from March 1986 to March 1988.

The RD-274, which is of four autonomous single-chamber motor blocks. Designed under the guidance of Valentin Glushko and Vitaly Radovsky. RD-0255 engine, made according to a closed circuit. The rocket engine was developed under the guidance of Alexander Konopatov. The second-stage steering engine has four engines. The components of fuel are UDMH and nitrogen tetroxide. Scientific Research Institute-692 (NPO “Khartron”) Vladimir Sergeyev. The unified KP was developed at the CDB TM under the leadership of Boris Aksyutin. Of overwhelming the enemy’s defense system.

Mass production of missiles deployed in Dnepropetrovsk.

TTX rocket “Voivode” P-36M2. 15A18M
Maximum firing range of a rocket with a MIRV ID 11,000 km
Maximum range of missiles with monoblock warhead 15,000 km
Maximum starting weight 211 t
Head mass 8.8 t
Rocket length 34.3 m
Maximum case diameter 3m
Traction propulsion engine first stage on the ground 144 tf
Specific impulse of the engine 296 kgf · s / kg
Initially set warranty period 15 years.

MR-UR-100. 15A15 (PC-16A) [SS-17. Spanker]

The MR-UR-100 is a two-stage intercontinental ballistic missile. It was equipped with an ICF with four warheads and a single-block warhead. Developed by Yuzhnoye Design Bureau under the direction of Mikhail Yangel and Vladimir Utkin. Project development started in 1967. September 19, 1969. Flight design tests test at Baikonur test site. The complex was put into service on December 30, 1975. Put on combat duty May 6, 1975.

Under the direction of Alexey Utkin. Start method – mortar. The unified mine-type protection has been developed under the direction of Nikolai Krivoshein and Boris Aksyutin. RD-268, made according to a closed circuit. The steering engine has four rotary combustion chambers. The first-stage march engine has been developed. The second stage is equipped with a single-chamber fixed-mounted engine 15D169, developed in KB-4 by Yuzhnoye Design Bureau. There are nozzles and four steering nozzles. The components of fuel are UDMH and nitrogen tetroxide. The dilution of warheads is carried out using a solid-propellant rocket engine. The control system is autonomous, inertial. Under the leadership of Nikolai Pilyugin. Gyroscopic devices have been developed under the direction of Viktor Kuznetsov. He was the chief designer of the Soyuz LNPO. The weapons were developed by the Central Scientific Research Institute of Radiological Research. For the missile systems MR-UR-100, R-36M and UR-100N, the Leningrad NPO Impuls developed for unified automated combat control system.

Mass production of missiles deployed in 1973.

TTX rocket MR-UR-100. 15A15
Maximum firing range of a rocket with a MIRV ID 10,200 km
Maximum range of missiles with monoblock warhead 10,300 km
Maximum starting weight 71 t
Head mass 2.5 t
Rocket length 21 m
The maximum diameter of the body 2.25 m
Maximum diameter of the second stage casing 2.1 m
Traction propulsion engine first stage on the ground 117 tf
Specific impulse of the engine 296 kgf · s / kg
Initially set warranty period 10 years

MR-UR-100 UTTH. 15A16 (PC-16B) [SS-17. Spanker]

MR-UR-100 UTTH is a two-stage intercontinental ballistic missile. It was equipped with an ICF with four warheads and a single-block warhead. Developed in Yuzhnoye design under the direction of Vladimir Utkin. Development started August 16, 1976. Flight design tests from October 25, 1977 to December 15, 1979 at the Baikonur test site. The complex was put on combat duty on October 17, 1978. Adopted on December 17, 1980.

The characteristics of the MR-UR-100 UTTH rocket are the MR-UR-100.

“Perimeter” 15A11

“Perimeter” – a command rocket. It was in accordance with the decree of August 30, 1974. In December 1975, it was developed.

In December 1977, a conceptual design was developed for a command missile 15A11 of the Perimeter system. In December 1979, the first launches of the missiles were in a special period. In March 1982, the flight tests of the rocket were completed.

UR-100N. 15A30 (PC-18A) [SS-19. Stilleto]

The UR-100N is a two-stage intercontinental ballistic missile. Equipped with a multiple rocket launcher with six warheads. Developed in the Central Design Bureau of Mechanical Engineering. 1 of the TsKBM under the leadership of Viktor Bugaysky. Development started on September 2, 1969. Tests were conducted from April 9, 1973 to October 1975. April 26, 1975. Adopted on December 30, 1975.

The SSU OS has been developed at the Branch No. 2 of the TsKBM (State Research and Design Institute “OKB Vympel”) under the leadership of Vladimir Baryshev. Starting method – gasdynamic. LRE RD-0233 and RD-0234. Engines are made in a closed circuit. For the second stage, they were created: RD-0235, made according to a closed scheme, and RD-0236, made according to a open scheme. The second stage propulsion engine is stationary. LREs and combat-level LREs were developed by the Alexander Konopatov. The second stage is controlled by a steering engine with four rotary combustion chambers. The components of fuel are UDMH and nitrogen tetroxide. Brake engines are developed in KB-2 of Plant No. 81 (ICB Iskra) under the leadership of Ivan Kartukov. The autonomous inertial control system was developed under the leadership of Vladimir Sergeev.

Serial production of missiles launched in 1974 at the Moscow Machine-Building Plant named after MV Khrunichev.

TTX missiles UR-100N. 15A30
Maximum firing range 10,000 km
Rocket length 24.3 m
Maximum case diameter 2.5 m
Starting weight 105.6 t
Head mass 4,350 kg

UR-100N UTH. 15A35 (PC-18B) [SS-19. Stilleto]

UTTH UR-100N is a two-stage intercontinental ballistic missile. Equipped with a multiple rocket launcher with six warheads. Chelomey and Herbert Efremov. Development started August 16, 1976. The tests were carried out from December 1977 to June 1979. The building was named after M. Khrunichev lasted until 1985.

The characteristics of the UR-100N UTTH rocket.

RT-23. 15F43

RT-23. 15Zh43 – A three-stage intercontinental ballistic missile. He was carrying out a ruling on January 13, 1969. In October 1975, the ICBM began to build on.

RT-23. 15F44

RT-23. 15Zh44 – a three-stage solid propellant intercontinental ballistic missile for mine launchers. July 23, 1976. Vladimir Lapygin.
The first draft of the warhead was completed in March 1977. On June 1, 1979, MIRR-IN missile. The design of the rocket with the MIRP ID 15F143 has been approved in December 1979. rocket RT-23. 15Zh44 not adopted.

RT-23. 15ZH52 (PC-22) [SS-24. Scalpel]

RT-23.15Zh52 – a three-stage solid fuel intercontinental ballistic missile for BZHRK. Equipped with a wringer with ten warheads. Developed by Yuzhnoye Design Bureau under the direction of Mikhail Yangel and Vladimir Utkin. Development started in 1976. July 6, 1979. But it wasn’t accepted for service.

He was an autonomous undergraduate of Vladimir Lapygin. The launcher was developed under the direction of Alexey Utkin. Start method – mortar. It’s a challenge to overcome the missile defense system. Mixed fuel and solid-propellant were developed in Dzerzhinsky under the direction of Boris Zhukov. The command module was developed at TsKBTM under the leadership of Boris Aksyutin and Alexander Leontenkov.

The assembly of the missiles was mastered at the Pavlograd mechanical plant. The railway launcher was mass-produced by the Yurga Machine-Building Plant.

TTX rocket RT-23 15F52
Maximum firing range 10,000 km
Maximum starting weight 104 t
Missile mass in TPK 126 t
Head mass 4.05 t
Number of nuclear warheads ten
Rocket length 22 m
Maximum case diameter 2.4 m

“Well done” RT-23UTTH. 15ZH60 (PC-22) [SS-24. Scalpel]

RT-23 UTTH – a solid three-stage intercontinental ballistic missile for three types of basing. Equipped with a wringer with ten warheads. Utkin on August 9, 1983. Tests of the mine version 15ZH60 at the Plesetsk test site were sent from July 31, 1986 to September 26, 1988. Adopted on November 28, 1989.
The silo was developed at the Vympel State Research and Production Institute. Start method – mortar. He was an autonomous undergraduate of Vladimir Lapygin. Mixed fuel and solid-propellant were developed in Dzerzhinsky under the direction of Boris Zhukov. Chemical transport engineering engineering. It is a strategy of overcoming missile defense.

Topol-M (SS-27)

The Topol-M missile system (SS-27) was developed at the Moscow Institute of Heating Engineering. The complex is being created in the mobile-based variant. It was the completion of the deployment of the complex. The rocket of the Topol-M complex is a three-stage solid propellant, created in the monoblock variant. The production of rockets is carried out by the Votkinsk engineering plant.

Three engines of missiles. In addition, there were several engines for the enemy.

Performance characteristics of the Topol-M missile system:
Rocket length (along with the head) 22.7 m
Diameter 1.95 m
Starting weight 47.2 t
Combat load 1.2 t
Range of flight more than 10 thousand km

P-1. 8A11 [SS-1. Scunner]

R-1 – single-stage tactical ballistic missile (long-range ballistic missile). Developed at NII-88 under the direction of Sergey Korolev. Chief Designer – Alexander Shcherbakov. It was a test on the 14th day of April 19, 1948. Tests at the Kapovin Yar test site were conducted from September 17, 1948 to October 1949.
Marching single-chamber LRE RD-100 (8D51) was developed in OKB-456 under the direction of Valentina Glushko. It is ethyl alcohol and liquid oxygen. The GSKB Spetsmash has been developed under the direction of Vladimir Barmin. Starting device – fixed ground table. Start method – gas-dynamic (start was carried out by the main engine). The control system is autonomous, inertial. Developed at NII-885 under the direction of NII-944 under the direction of Viktor Kuznetsov. Under the leadership of Anatoly Gurevich. The rocket installer has been developed at Nikolay Leikin. Fuel tanks suspended (non-bearing). Controls – air and gas jet rudders. The missile has a monoblock non-nuclear non-detachable head in flight.
Missile production is deployed at the Experimental Plant NII-88 at Podlipki. Serial production of R-1 missiles and RD-100 586 in Dnepropetrovsk.

TTX rocket P-1. 8А11
Maximum firing range 270 km
Maximum starting weight 13.4 t
Rocket dry mass 4 t
Head mass 1 t
Of the explosives 785 kg
Mass of fuel 8.5 t
Rocket length 14.6 m
Maximum case diameter 1.65 m
Traction engine on the ground 27 tf
Thrust propulsion engine in the void 31 tf
Specific impulse thrust sustainer engine at the ground 199 kgf · s / kg
Specific impulse of the engine in a vacuum 232 kgf · s / kg
Main Engine Hours 206 s.
Main engine mass 885 kg

P-2. 8F38 [SS-2. Sibling]

R-2 – single-stage operational-tactical ballistic missile (long-range ballistic missile). Developed at NII-88 under the direction of Sergey Korolev. Sergey Korolev began in 1946. It was issued on April 14, 1947., 1947. Tests were conducted from September 21, 1949 to July 1951. The complex was put into service on November 27, 1951.

Marching single-chamber LRE RD-101 (8D52) was developed in OKB-456 under the direction of Valentina Glushko. It is ethyl alcohol and liquid oxygen. The GSKB Spetsmash has been developed under the direction of Vladimir Barmin. Starting device – stationary ground launch pad. Starting method – gasdynamic. Under the leadership of Anatoly Gurevich. The installer was developed at the Central Design Bureau of Heavy Machinery under the direction of Nikolay Leikin. The autonomous inertial control system was developed at the NII-885 under the direction of Viktor Kuznetsov. Mikhail Borisenko. Missile controls – air and gas jet rudders. Fuel tank – bearing, oxidizer tank – suspended. The rocket has a monoblock non-nuclear detachable head in flight.

Serial production of R-2 missiles and RD-101 engines was deployed 586 in Dnepropetrovsk in June 1953.

TTX rocket R-2. 8F38
Maximum firing range 600 km
Maximum starting weight 20.4 t
Head mass 1.5 t
Of the explosives 1 008 kg
Mass of fuel 14.5 t
Rocket length 17.7 m
Maximum case diameter 1.65 m
Traction engine on the ground 37 tf
Thrust propulsion engine in the void 41 tf
Specific impulse thrust sustainer engine at the ground 210 kgf · s / kg
Specific impulse of the engine in a vacuum 237 kgf · s / kg
Main engine mass 1,178 kg

P-3. 8A67

The P-3 is a single-stage long-range ballistic missile (long-range ballistic missile). Under the leadership of Sergei Korolev from April 14, 1947. It was approved on December 7, 1949. On the October 4, 1950s, the R-3 ballistic missile is up to 3,000 km away. In December 1951, S.P. Korolev ce-work P-5.

Marching single-chamber LRE RD-110 was developed in OKB-456 under the direction of Valentin Glushko. The fuel components are oxygen and kerosene. The complex of ground-based facilities was developed at the GSKB Spetsmash under the leadership of Vladimir Barmin. Starting device – stationary ground launch pad. Starting method – gasdynamic. It was developed under NII-885 under the leadership of Boris Konoplev. Command devices (gyroscopes) were developed at SRI-944 under the leadership of Viktor Kuznetsov.

TTX rocket P-3 8A67
Maximum firing range 3000 km
Rocket length 27 m
Maximum case diameter 2.8 m
Thrust propulsion engine 120 tf
Specific impulse of the engine thrust 243 kgf · s / kg

P-5. 8A62 [SS-3. Shyster]

R-5 – single-stage medium range ballistic missile (long-range ballistic missile). Developed at NII-88 under the direction of Sergey Korolev. Lead Designer – Dmitry Kozlov. Development kicks in 1949. Tests were held from April 2, 1953 to February 1955. In 1954, based on the R-5 rocket, the development of the R-5M rocket began.
Marching single-chamber engine RD-103 (8D54) was developed in OKB-456 under the direction of chief designer Valentin Glushko. It is ethyl alcohol and liquid oxygen. The launching device – a stationary ground-based launcher – was developed at Spetsmash under the supervision of Vladimir Barmin. Starting method – gasdynamic. Inertial control system with radio correction of the flight trajectory. The inertial SS was developed at NII-885 under the direction of Viktor Kuznetsov. The radio control system was developed at the SRI-20 under the leadership of Boris Konoplev. Controls – gas-jet and aerodynamic control surfaces. The rocket has a monoblock non-nuclear detachable head in flight. Pilot production of missiles mastered at the Experimental Plant NII-88.

TTX rocket R-5 8A62
Maximum firing range 1,200 km
Maximum starting weight 26 – 28.5 t
Head mass 1.42 t
The mass of the unfilled rocket 4.2 t
Rocket length 20.75 m
Maximum case diameter 1.65 m
Altitude of 90 km about 3 km / s
Traction engine on the ground 44 tf
Thrust propulsion engine in the void 50 tf
Specific impulse thrust sustainer engine at the ground 220 kgf · s / kg
Specific impulse of the engine in a vacuum 243 kgf · s / kg
Main Engine Hours 219 seconds
Main engine mass 870 kg

R-5M. 8K51 [SS-3. Shyster]

R-5M – single-stage medium range ballistic missile (long-range ballistic missile). Developed in OKB-1 under the leadership of Sergei Korolev. Lead Designer – Dmitry Kozlov. Development started on April 10, 1954. Tests were held from January 20, 1955 to February 1956. Tests were held on June 21, 1956.

Marching single-chamber engine RD-103M developed in OKB-456 under the direction of Valentine Glushko. Ground launch complex developed in GSKB Spetsmash under the leadership of Vladimir Barmin. Transport units developed in KBTM under the leadership of Vladimir Petrov. The rocket installer was developed at TsKB TM under the direction of Nikolay Krivoshein. He worked on the NII-885 under the leadership of Viktor Kuznetsov. The radio control system was developed at the SRI-20 under the leadership of Boris Konoplev. Controls – air and gas jet rudders. Nuclear miss detachable head in flight. The nuclear warhead was developed in Arzamas-16 under the leadership of Samvel Kocharyants. The nuclear warheads were created at the Moscow Branch. 1 (now the All-Russian Research Institute of Automation named after NL Dukhov) KB-11 (Arzamas-16) under the direction of Nikolai Dukhov and Victor Zuevsky.

Serial production of rockets and engines 586 in Dnepropetrovsk.

TTX rocket R-5M 8K51
Maximum firing range 1,200 km
Maximum starting weight 29.1 t
Head mass 1.35 t
Nuclear warhead power 300 kt (there are data
about warheads power
80 kt and 1 Mt)
The mass of the unfilled rocket 4.39 t
Mass of fuel, hydrogen peroxide and compressed air 24.5 tons
Mass of liquid oxygen 13.99 t
Mass of ethanol 10.01 t
Rocket length 20.75 m
Maximum case diameter 1.65 m
Rocket speed at engine shutdown 3,016 m / s
Top of the trajectory 304 km
Flight time to destination 637 seconds
Traction engine on the ground 43 tf
Thrust propulsion engine in the void 50 tf
Specific impulse thrust sustainer engine at the ground 216 kgf · s / kg
Specific impulse of the engine in a vacuum 243 kgf · s / kg
Main engine mass 870 kg

R-7. 8K71 [SS-6. Sapwood]

The R-7 is a two-stage intercontinental ballistic missile. Developed in OKB-1 under the leadership of Sergei Korolev. Lead Designer – Dmitry Kozlov. Development started May 20, 1954. Tests were held on May 15, 1957 to June 1958. Tests were carried out on January 20, 1960, but did not put on combat.
The first stage (four side blocks) LRE RD-107 (8D74) and four steering two-chamber engines. LRE RD-108 (8D75) and a four-chamber steering engine. Marching engines RD-107 and RD-108 are developed in OKB-456 under the direction of Valentin Glushko. Steering engines are developed in OKB-1 under the direction of Mikhail Melnikov. The fuel components are kerosene T-1 and liquid oxygen. The launching device – a stationary ground-based launcher – was developed at Spetsmash under the supervision of Vladimir Barmin. Starting method – gasdynamic. The transport units of the complex were developed at KBTM under the leadership of Vladimir Petrov. Ground maintenance units are developed at the Central Design Bureau of Heavy Machinery under the direction of Nikolay Krivoshein. Inertial control system with radio correction of the flight trajectory. The autonomous control system was developed at NII-885 under the direction of Nikolay Pilyugin. The radio control system was developed at NII-885 under the direction of Mikhail Ryazansky. Command devices were developed at Scientific Research Institute-944 under the direction of Viktor Kuznetsov. Missile controls – steering engines and air rudders. Under the leadership of Andronik Iosifyan. Nuclear miss detachable head in flight. It was Samvel Kocharyants.
Pilot production OKB-1 in Podlipkah. Serial production of rockets was launched in 1958 at the Kuibyshev Aviation Plant. 1. Production of the first and second-stage propulsion engines was deployed at the Kuibyshev Engine-Building Plant No. 24 named after M.V. Frunze.

TTX rocket R-7 8K71
Maximum firing range 9 500 km
Maximum starting weight 283 t
Dry mass of the rocket 27 t
Head mass 5.4 t
Nuclear warhead power 3 Mt (5 Mt)
Mass of fuel 250 t
Rocket length 31 – 33 m
The length of the central unit of the rocket 19.2 m
Conical head length 3.5 m
Maximum transverse size of the assembled package 10.3 m
Traction propulsion engine first stage on the ground 82 tf
Thrust propulsion engine first stage in the void 100 tf
Specific impulse thrust sustainer engine first stage on the ground 252 kgf · s / kg
Specific impulse thrust sustainer engine first stage in a vacuum 308 kgf · s / kg
Running time of side engine sustainer engines (first stage) 120 s
Mass of the first stage main engine 1,155 kg
Traction propulsion engine second stage on the ground 75 tf
Traction propulsion engine second stage in the void 94 tf
Specific Impulse 243 kgf · s / kg
Specific Impulse 309 kgf · s / kg
The second unit up to 290 s
Mass of the second stage propulsion engine 1,250 kg

R-7A. 8K74 [SS-6. Sapwood]

The R-7A is a two-stage intercontinental ballistic missile. Developed in OKB-1 under the leadership of Sergei Korolev. Lead Designer – Dmitry Kozlov. Development started on July 2, 1958. Tests at the Baikonur test site were held from December 24, 1958 to July 1960. On January 1, 1960. Adopted on September 12, 1960.
The first stage (four side blocks) LRE RD-107 and four steering two-chamber engines. RD-108 and a four-chamber steering engine. Marching engines RD-107 and RD-108 are developed in OKB-456 under the direction of Valentin Glushko. Steering engines are developed in OKB-1 under the direction of Mikhail Melnikov. The fuel components are kerosene T-1 and liquid oxygen. The launching device – a stationary ground-based launcher – was developed at Spetsmash under the supervision of Vladimir Barmin. Starting method – gasdynamic. The transport units of the complex were developed at KBTM under the leadership of Vladimir Petrov. Ground maintenance units were developed at the Central Design Bureau of Heavy Machinery under the direction of Nikolay Krivoshein. Inertial control system with radio correction of the flight trajectory. The autonomous control system was developed at NII-885 under the direction of Nikolay Pilyugin. The radio control system was developed at NII-885 under the direction of Mikhail Ryazansky. Command devices were developed at Scientific Research Institute-944 under the direction of Viktor Kuznetsov. Missile controls – steering engines and air rudders. The Andronik Iosif’yan electrical equipment complex has been developed. Nuclear miss detachable head in flight. It was Samvel Kocharyants.
Serial production of rockets is deployed at the Kuibyshev Aviation Plant No. 1. Production of the first and second stage cruise engines is deployed at the Kuibyshev Engine-Building Plant No. 24 named after M.V. Frunze.

TTX rocket R-7A 8K74
Maximum firing range 9 500 km
Maximum starting weight 276 t
Head mass 3.7 t
Nuclear warhead power 3 mt
Mass of fuel 250 t
Rocket length 31.4 m
Maximum diameter package package 10.3 m
Traction propulsion engine first stage on the ground 82 tf
Thrust propulsion engine first stage in the void 100 tf
Specific impulse thrust sustainer engine first stage on the ground 252 kgf · s / kg
Specific impulse thrust sustainer engine first stage in a vacuum 308 kgf · s / kg
Mass of the first stage main engine 1,155 kg
Traction propulsion engine second stage on the ground 75 tf
Traction propulsion engine second stage in the void 94 tf
Specific Impulse 243 kgf · s / kg
Specific Impulse 309 kgf · s / kg
Mass of the second stage propulsion engine 1,250 kg

Perspectives and Trends

It’s not a problem. There is a clear understanding of the government and the government. The Supreme Commander of Armed Forces, VV. President of the Russian Federation. Didn’t need to be a trainer.

It was the time of the decade. It has been noted that this is the case. He was “dry” missiles (“Stiletto”) was organized. As the survey showed, despite the signs of aging, these missiles are not observed. It’s possible that it’s not a problem. This work was highly appreciated by V.V. At the meeting, he said, “… Russia has a significant stock of land-based strategic missiles.”

This year’s has been coming for years.

After 2015, it will be mine-based and mobile combat systems. The number of these missile systems. So these days, in regards to the Saratov region, will be taken up combat combat.

It has been possible to address threats and threats. But it shouldn’t be 10 to 15 years. We still have such a margin of time.

For example, military-strategic realities.

By December 31, 2012, the warheads should be no more than 1,700-2.200. For example, it can be a question. it should be noted.

How it works nuclear weapon, read here.

Finds out how to significantly increase your chances of surviving a nuclear attack:

  • Protection against weapons of mass destruction
  • Rules of conduct for emergencies: Shelling by conventional weapons
  • Rules of conduct

You can also find out about the “Caliber” rocket, which is gained through the ISIS.

Strategic Missile Forces: Strategic Missile Forces

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