Intercontinental ballistic missile: how it works. Land-based intercontinental ballistic missiles of Russia and foreign countries (rating) Russian intercontinental ballistic missiles

07.03.2020

Intercontinental ballistic missiles (ICBMs) are the primary means of nuclear deterrence. The following countries have this type of weapon: Russia, USA, Great Britain, France, China. Israel does not deny that it has such types of missiles, but it does not officially confirm it either, but it has the capabilities and well-known developments to create such a missile.

Below is a list of ICBMs ranked by maximum range.

1. P-36M (SS-18 Satan), Russia (USSR) - 16,000 km

The P-36M (SS-18 Satan) is an intercontinental missile with the world's longest range of 16,000 km. Hit accuracy 1300 meters.
Starting weight 183 tons. The maximum range is achieved with a warhead mass of up to 4 tons, with a warhead mass of 5825 kg, the missile flight range is 10200 kilometers. The missile can be equipped with multiple and monoblock warheads. To protect against missile defense (ABM), when approaching the affected area, the missile throws out decoys for missile defense. The rocket was developed at the Yuzhnoye Design Bureau named after M.V. M. K. Yangelya, Dnepropetrovsk, Ukraine. The main basing of the rocket is mine.
The first R-36Ms entered the USSR Strategic Missile Forces in 1978.
The rocket is two-stage, with liquid propellant rocket engines providing a speed of about 7.9 km/sec. Withdrawn from service in 1982, replaced by a next-generation missile based on the R-36M, but with increased accuracy and ability to overcome missile defense systems. Currently, the rocket is used for peaceful purposes, for launching satellites into orbit. The created civilian rocket was named Dnepr.

2. DongFeng 5А (DF-5A), China - 13,000 km.

The DongFeng 5A (NATO reporting name: CSS-4) has the longest range among the Chinese Army's ICBMs. Its flight range is 13,000 km.
The missile was designed to be capable of hitting targets within the continental United States (CONUS). The DF-5A missile entered service in 1983.
The missile can carry six warheads weighing 600 kg each.
The inertial guidance system and on-board computers provide the desired direction of the missile's flight. Rocket engines are two-stage with liquid fuel.

3. R-29RMU2 Sineva (RSM-54, according to NATO classification SS-N-23 Skiff), Russia - 11,547 kilometers

The R-29RMU2 Sineva, also known as the RSM-54 (NATO code name: SS-N-23 Skiff), is a third-generation intercontinental ballistic missile. The main missile base is submarines. Sineva showed a maximum range of 11,547 kilometers during testing.
The missile entered service in 2007 and is expected to be in use until 2030. The missile is capable of carrying four to ten individually targetable warheads. The Russian GLONASS system is used for flight control. Targets are hit with high accuracy.
The rocket is three-stage, liquid-propellant jet engines are installed.

4. UGM-133A Trident II (D5), USA - 11,300 kilometers

The UGM-133A Trident II is an ICBM designed for submarine deployment.
The missile submarines are currently based on the Ohio (USA) and Wangard (UK) submarines. In the United States, this missile will be in service until 2042.
The first launch of UGM-133A was carried out from the launch site at Cape Canaveral in January 1987. The missile was adopted by the US Navy in 1990. UGM-133A can be equipped with eight warheads for various purposes.
The missile is equipped with three solid rocket motors, providing a range of up to 11,300 kilometers. It is distinguished by high reliability, so during the tests 156 launches were carried out and only 4 of them were unsuccessful, and 134 launches in a row were successful.

5. DongFeng 31 (DF-31A), China - 11,200 km

DongFeng 31A or DF-31A (NATO reporting name: CSS-9 Mod-2) is a Chinese intercontinental ballistic missile with a range of 11,200 kilometers.
The modification was developed on the basis of the DF-31 missile.
The DF-31A missile has been put into operation since 2006. Based on Julang-2 (JL-2) submarines. Modifications of ground-based missiles on a mobile launcher (TEL) are also being developed.
The three-stage rocket has a launch weight of 42 tons and is equipped with solid propellant rocket engines.

6. RT-2PM2 "Topol-M", Russia - 11,000 km

RT-2PM2 "Topol-M", according to NATO classification - SS-27 Sickle B with a range of about 11,000 kilometers, is an improved version of the Topol ICBM. The missile is installed on mobile launchers, and the silo-based version can also be used.
The total mass of the rocket is 47.2 tons. It was developed at the Moscow Institute of Thermal Engineering. Produced at the Votkinsk Machine-Building Plant. This is the first ICBM in Russia, which was developed after the collapse of the Soviet Union.
A missile in flight is capable of withstanding powerful radiation, an electromagnetic pulse, and a nuclear explosion in close proximity. There is also protection against high-energy lasers. When flying, it maneuvers thanks to additional engines.
Three-stage rocket engines use solid fuel, the maximum rocket speed is 7,320 meters / sec. Tests of the missile began in 1994, adopted by the Strategic Missile Forces in 2000.

7. LGM-30G Minuteman III, USA - 10,000 km

The LGM-30G Minuteman III has an estimated range of 6,000 kilometers to 10,000 kilometers, depending on the type of warhead. This missile entered service in 1970 and is the oldest missile in service in the world. It is also the only silo-based missile in the United States.
The first rocket launch took place in February 1961, modifications II and III were launched in 1964 and 1968, respectively.
The rocket weighs about 34,473 kilograms and is equipped with three solid propellant engines. Rocket flight speed 24 140 km / h

8. M51, France - 10,000 km

The M51 is an intercontinental range missile. Designed for basing and launching from submarines.
Produced by EADS Astrium Space Transportation, for the French Navy. Designed to replace the M45 ICBM.
The missile was put into operation in 2010.
Based on Triomphant-class submarines of the French Navy.
Its combat range is from 8,000 km to 10,000 km. An improved version with new nuclear warheads is scheduled to enter service in 2015.
The M51 weighs 50 tons and can carry six individually targetable warheads.
The rocket uses a solid propellant engine.

9. UR-100N (SS-19 Stiletto), Russia - 10,000 km

UR-100N, according to the START treaty - RS-18A, according to NATO classification - SS-19 mod.1 Stiletto. This is the fourth generation ICBM, which is in service with the Russian Strategic Missile Forces.
The UR-100N entered service in 1975 and is expected to be in service until 2030.
Can carry up to six individually targetable warheads. It uses an inertial targeting system.
The missile is two-stage, based type - mine. Rocket engines use liquid propellant.

10. RSM-56 Bulava, Russia - 10,000 km

Mace or RSM-56 (NATO code name: SS-NX-32) is a new intercontinental missile designed for deployment on Russian Navy submarines. The missile has a range of up to 10,000 km and is intended for Borey-class nuclear submarines.
The Bulava missile was put into service in January 2013. Each missile can carry six to ten individual nuclear warheads. The total usable weight delivered is about 1,150 kg.
The rocket uses solid propellant for the first two stages and liquid propellant for the third stage.

Ballistic missiles have been and remain a reliable shield of Russia's national security. A shield, ready, if necessary, to turn into a sword.

R-36M "Satan"

Developer: Design Bureau Yuzhnoye
Length: 33.65 m
Diameter: 3 m
Starting weight: 208 300 kg
Flight range: 16000 km
Soviet strategic missile system of the third generation, with a heavy two-stage liquid-propellant, ampulized intercontinental ballistic missile 15A14 for placement in a silo launcher 15P714 of increased security type OS.

The Americans called the Soviet strategic missile system "Satan". At the time of the first test in 1973, this missile became the most powerful ballistic system ever developed. Not a single missile defense system was able to withstand the SS-18, the radius of destruction of which was as much as 16 thousand meters. After the creation of the R-36M, the Soviet Union could not be worried about the "arms race". However, in the 1980s, the Satan was modified, and in 1988, a new version of the SS-18, the R-36M2 Voyevoda, entered service with the Soviet army, against which even modern American missile defense systems cannot do anything.

RT-2PM2. "Topol M"

Length: 22.7 m
Diameter: 1.86 m
Starting weight: 47.1 t
Flight range: 11000 km

The RT-2PM2 rocket is made in the form of a three-stage rocket with a powerful mixed solid-propellant power plant and a fiberglass body. Rocket testing began in 1994. The first launch was carried out from a silo launcher at the Plesetsk cosmodrome on December 20, 1994. In 1997, after four successful launches, mass production of these missiles began. The act on the adoption by the Strategic Missile Forces of the Russian Federation of the Topol-M intercontinental ballistic missile was approved by the State Commission on April 28, 2000. As of the end of 2012, there were 60 mine-based and 18 mobile-based Topol-M missiles on combat duty. All silo-based missiles are on combat duty in the Taman missile division (Svetly, Saratov region).

PC-24 "Yars"

Developer: MIT
Length: 23 m
Diameter: 2 m
Flight range: 11000 km
The first rocket launch took place in 2007. Unlike Topol-M, it has multiple warheads. In addition to warheads, Yars also carries a set of missile defense breakthrough tools, which makes it difficult for the enemy to detect and intercept it. This innovation makes the RS-24 the most successful combat missile in the context of the deployment of the global American missile defense system.

SRK UR-100N UTTH with 15A35 rocket

Developer: Central Design Bureau of Mechanical Engineering
Length: 24.3 m
Diameter: 2.5m
Starting weight: 105.6 t
Flight range: 10000 km
Intercontinental ballistic liquid rocket 15A30 (UR-100N) of the third generation with a multiple reentry vehicle (MIRV) was developed at the Central Design Bureau of Mechanical Engineering under the leadership of V.N. Chelomey. Flight design tests of the ICBM 15A30 were carried out at the Baikonur training ground (chairman of the state commission - Lieutenant General E.B. Volkov). The first launch of the ICBM 15A30 took place on April 9, 1973. According to official data, as of July 2009, the Strategic Missile Forces of the Russian Federation had 70 deployed 15A35 ICBMs: 1. 60th Missile Division (Tatishchevo), 41 UR-100N UTTKh UR-100N UTTH.

15Ж60 "Well done"

Developer: Design Bureau Yuzhnoye
Length: 22.6 m
Diameter: 2.4m
Starting weight: 104.5 t
Flight range: 10000 km
RT-23 UTTH "Molodets" - strategic missile systems with solid-fuel three-stage intercontinental ballistic missiles 15Zh61 and 15Zh60, mobile railway and stationary mine-based, respectively. It was a further development of the RT-23 complex. They were put into service in 1987. Aerodynamic rudders are placed on the outer surface of the fairing, allowing you to control the rocket in a roll in the areas of operation of the first and second stages. After passing through the dense layers of the atmosphere, the fairing is reset.

R-30 "Mace"

Developer: MIT
Length: 11.5 m
Diameter: 2 m
Starting weight: 36.8 tons.
Flight range: 9300 km
Russian solid-propellant ballistic missile of the D-30 complex for placement on Project 955 submarines. The first launch of the Bulava took place in 2005. Domestic authors often criticize the Bulava missile system under development for a fairly large proportion of unsuccessful tests. According to critics, the Bulava appeared due to Russia's banal desire to save money: the country's desire to reduce development costs by unifying the Bulava with land-based missiles made its production cheaper , than usual.

X-101/X-102

Developer: MKB "Rainbow"
Length: 7.45 m
Diameter: 742 mm
Wingspan: 3 m
Starting weight: 2200-2400
Flight range: 5000-5500 km
New generation strategic cruise missile. Its hull is a low-wing aircraft, but has a flattened cross-section and side surfaces. The warhead of a rocket weighing 400 kg can hit 2 targets at once at a distance of 100 km from each other. The first target will be hit by ammunition descending on a parachute, and the second one directly when a missile hits. With a flight range of 5000 km, the circular probable deviation (CEP) is only 5-6 meters, and with a range of 10,000 km does not exceed 10 m.

North Korean leader Kim Jong-un said that the country's security must be ensured by "offensive" measures. At the same time, he previously noted that the republic would take steps to strengthen its armed forces. Experts recall that in December, the DPRK reported tests twice, but did not specify what exactly. According to analysts, in this way the North Korean authorities want to push the United States to continue the dialogue, which has stalled due to Washington's unwillingness to make concessions.

The Chinese army has flight-tested a new sea-launched ballistic missile capable of "hitting a nuclear warhead across the United States," reports The Washington Times, citing Pentagon sources.

45 years ago, the first regiment armed with the R-36M intercontinental ballistic missile (ICBM), nicknamed "Satan" in NATO and the status of the most powerful strategic complex in the world, took up combat duty. The missile could carry more than 8 tons of payload, breaking through the enemy missile defense system. Depending on the equipment, the R-36M could hit objects at a distance of up to 15,000 km. In the late 1980s, for the needs of the Strategic Missile Forces, a modernized version of the "Satan" was developed, which is still in service with the strategic forces of the Russian Federation. Now the RS-28 Sarmat is being created to replace it. According to experts, it is no coincidence that "Satan" has earned such a frightening name in the West. The capabilities of this ICBM make it almost guaranteed to hit the most important targets on enemy territory.

The army and navy of Russia must always be equipped with the most modern weapons. This was stated by Russian President Vladimir Putin at a meeting of the expanded collegium of the Ministry of Defense. According to him, in the past year, the share of new military equipment in the Armed Forces was 68%, and in 2020 it will increase to 70%. As Putin stressed, qualitative changes have taken place in command and control, robotics and unmanned aircraft. At the same time, there is concern about Washington's destruction of the arms control system. Moscow will take this situation into account in the state defense plan for 2020. According to experts, the current state of the Russian Armed Forces and the pace of rearmament are adequate to modern challenges and threats to national security.
In December, the crews of the Peresvet mobile laser systems took up combat duty. This was stated by the Chief of the General Staff of the Armed Forces of the Russian Federation Valery Gerasimov. According to him, the unique Russian weapons will cover strategic mobile systems. According to experts, the main purpose of lasers will be air defense. "Peresvet" is the world's only combatant laser system capable of causing damage to aircraft. According to analysts, the unique weapon will become more compact in the future and will be modernized for wider use in the army.
60 years ago, a new type of armed forces was created in the structure of the Soviet army - the Strategic Missile Forces (RVSN). Huge resources invested in their formation allowed the USSR to achieve strategic parity with the United States, which remains to this day. The Strategic Missile Forces consist of three armies and 12 divisions, whose arsenal includes about 400 silo- and mobile-based intercontinental ballistic missiles. It is expected that by 2024 the Strategic Missile Forces units will be 100% equipped with modern Russian-made complexes. According to experts, maintaining the high combat readiness of this type of troops is the main guarantor of the national security of the Russian Federation.
The Strategic Missile Forces are preparing to put into service the latest intercontinental ballistic missile (ICBM) RS-28 Sarmat. This was stated in an interview with the Krasnaya Zvezda newspaper by Colonel-General Sergei Karakaev, commander of this branch of the Armed Forces. The first recipient of this unique complex will be one of the regiments of the Uzhur missile division. "Sarmat" should replace in the troops of the R-36M2 "Voevoda" ICBM, which has been on combat duty since the late 1980s. The RS-28 will have an almost unlimited range and will be able to carry up to 10 tons of payload. According to experts, the appearance of "Sarmat" in the arsenal of the Strategic Missile Forces will allow Russia to maintain strategic parity with the United States.
The aggravation of existing interstate contradictions in the Arctic can lead to an armed conflict, but the scenario of a large-scale confrontation is excluded. This was stated by the commander of the Northern Fleet (SF), Vice Admiral Alexander Moiseev, speaking at the forum "Arctic: present and future". He called the policy of the United States and other Western states the key destabilizing factor. According to the RF Ministry of Defense, since 2015 the intensity of operational and combat training of NATO troops in high latitudes has doubled. In this regard, Russia is pursuing a policy of strengthening the strike and anti-aircraft capabilities of the Northern Fleet.
The Council of the European Union approved 13 new programs under the Permanent Structured Cooperation on Security and Defense (PESCO). Among them is the TWISTER project, aimed at creating a threat detection and tracking system that should strengthen Europe's missile defense capabilities. Analysts note that European countries could take care of the issue of their own missile defense because of the US withdrawal from the INF Treaty. However, experts note that there is no talk yet about the creation by the EU states of full-fledged systems of such weapons.

Ballistic missiles have been and remain a reliable shield of Russia's national security. A shield, ready, if necessary, to turn into a sword.

R-36M "Satan"

RT-2PM2. "Topol M"

Length: 22.7 m
Diameter: 1.86 m
Starting weight: 47.1 t
Flight range: 11000 km

PC-24 "Yars"

SRK UR-100N UTTH with 15A35 rocket

15Ж60 "Well done"

R-30 "Mace"

X-101/X-102

Developer: MKB "Rainbow"
Length: 7.45 m
Diameter: 742mm
Wingspan: 3 m
Starting weight: 2200-2400
Flight range: 5000-5500 km
New generation strategic cruise missile. Its hull is a low-wing aircraft, but has a flattened cross-section and side surfaces. The warhead of a rocket weighing 400 kg can hit 2 targets at once at a distance of 100 km from each other. The first target will be hit by ammunition descending on a parachute, and the second one directly when a missile hits. With a flight range of 5000 km, the circular probable deviation (CEP) is only 5-6 meters, and with a range of 10,000 km does not exceed 10 m.

The book tells about the history of the creation and the present day of the strategic nuclear missile forces of the nuclear powers. The designs of intercontinental ballistic missiles, submarine ballistic missiles, medium-range missiles, and launch complexes are considered.

The publication was prepared by the department for the release of applications of the magazine of the Ministry of Defense of the Russian Federation "Army Collection" in conjunction with the National Center for Nuclear Risk Reduction and the publishing house "Arsenal-Press".

Tables with pictures.

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By the mid-1950s, almost simultaneously, the military leaders of the Soviet Union and the United States set their rocket designers the task of creating a ballistic missile capable of hitting targets located on another continent. The problem was not simple. It was necessary to solve a lot of complex technical issues related to ensuring the delivery of a nuclear charge to a distance of more than 9,000 km. And they had to be solved by trial and error.

Having come to power in N. S. Khrushchev, realizing the vulnerability of strategic aviation aircraft, he decided to find a worthy replacement for them. He bet on missiles. On May 20, 1954, a joint decree of the government and the Central Committee of the CPSU was issued on the creation of an intercontinental-range ballistic missile. The work was entrusted to TsKB-1. S.P. Korolev, who headed it, received broad powers to involve not only specialists from various industries, but also to use material resources. To conduct flight tests of intercontinental missiles, a new test base was needed, since the Kapustin Yar test site could not provide the required conditions. A government decree of February 12, 1955 laid the foundation for the creation of a new test site (now known as the Baikonur Cosmodrome) for testing the performance characteristics of ICBMs, launching satellites, and performing research and experimental work on the subject of rocket and space technology. A little later, in the area of \u200b\u200bthe Plesetsk station in the Arkhangelsk region, the construction of an object under the code name "" was launched, which was supposed to become the base of the first formation armed with new missiles (later it began to be used as a training ground and a spaceport). In difficult conditions, it was necessary to build launch complexes, technical positions, measuring points, access roads, residential and working premises. The main burden of the work fell on the military personnel of the construction battalions. The construction was carried out at an accelerated pace, and in two years the necessary conditions for testing were created.

By this time, the TsKB-1 team had created a rocket, which received the designation R-7 (8K71). The first test launch was scheduled for May 15, 1957 at 1900 Moscow time. As expected, it aroused great interest. All the chief designers of the rocket and the launch complex, program managers from the Ministry of Defense and a number of other organizations arrived. Everyone, of course, hoped for success. However, almost immediately after passing the command to start the propulsion system, a fire broke out in the tail compartment of one of the side blocks. The rocket exploded. Scheduled for June 11, the next launch of the "seven" did not take place due to a malfunction of the remote control of the central unit. It took the designers a month of hard and painstaking work to eliminate the causes of the identified problems. And on July 12, the rocket finally took off. Everything seemed to be going well, but only a few tens of seconds of flight had passed, and the rocket began to deviate from the given trajectory. A little later it had to be liquidated. As it was found out later, the cause was a violation of the missile's flight control along the rotation channels.

ICBM R-7A (USSR) 1960

The first launches showed the presence of serious flaws in the R-7 design.

When analyzing the telemetry data, it was found that at a certain moment, when the fuel tanks were empty, pressure fluctuations occurred in the flow lines, which led to increased dynamic loads and structural failure. To the credit of the designers, they quickly dealt with this defect.

The long-awaited success came on August 21, 1957, when the launched rocket fully completed its intended flight plan. And on August 27, a TASS message appeared in Soviet newspapers: “The other day, a new ultra-long-range multi-stage ballistic missile was launched. The tests were successful. They fully confirmed the correctness of the calculations and the chosen design ... The results obtained show that it is possible to launch missiles in any region of the globe. This statement, of course, did not go unnoticed abroad and produced the desired effect.

This success opened up broad prospects not only in the military field. At the end of May 1954, S.P. Korolev sent a letter to the Central Committee of the CPSU and the Council of Ministers of the USSR with a proposal to carry out the practical development of an artificial satellite of the Earth. N. S. Khrushchev approved this idea, and in February 1956, practical work began on the preparation of the first satellite and a ground-based measurement and control complex. On October 4, 1957, at 22.28 Moscow time, the R-7 rocket with the first artificial satellite on board launched and successfully put it into orbit. On November 3, the world's first biological satellite was launched, in the cockpit of which there was an experimental animal, the dog Laika. These events were of world importance and rightfully secured the priority of the Soviet Union in the field of space exploration.

In the meantime, combat missile testers faced new difficulties. Since the warhead rose to a height of several hundred kilometers, by the time it re-entered the dense layers of the atmosphere, it accelerated to enormous speeds. The round-shaped warhead, developed earlier, quickly burned out. In addition, it became clear that it was necessary to increase the maximum range of the missile and improve its operational characteristics.

On July 12, 1958, the assignment for the development of a more advanced missile, the R-7A, was approved. At the same time, the refinement of the "seven" was carried out. In January 1960, it was adopted by the newly created branch of the Armed Forces - the Strategic Missile Forces.

The two-stage rocket R-7 is made according to the "batch" scheme. Its first stage consisted of four side blocks, each 19 m long and with a maximum diameter of 3 m, located symmetrically around the central block (the second stage of the rocket) and connected to it by the upper and lower belts of power connections. The design of all blocks is the same: the tail compartment, the power ring, the compartment of the torus tanks for storing hydrogen peroxide used as the working fluid of the HP, the fuel tank, the oxidizer tank and the front compartment.

At the first stage, in each block, the RD-107 LRE was installed, designed by the GDL-OKB, with pumped supply of fuel components. It had six combustion chambers. Two of them were used as helmsmen. The rocket engine developed 78 tons of thrust near the ground and ensured operation at nominal mode for 140 seconds.

At the second stage, the RD-108 rocket engine was installed, similar in design to the RD-107, but differing mainly in the large number of steering chambers - 4. It developed thrust near the ground up to 71 tons and could operate in the main stage mode for 320 seconds.

Fuel for all engines was used two-component: oxidizer - liquid oxygen, fuel - kerosene. The ignition of the fuel at launch was carried out from pyrotechnic devices. To achieve the specified flight range, the designers installed an automatic system for regulating engine operation modes and a system for simultaneously emptying tanks (SOB), which made it possible to reduce the guaranteed fuel reserve. Previously, such systems were not used on missiles.

"Seven" was equipped with a combined control system. Its autonomous subsystem provided angular stabilization and stabilization of the center of mass in the active part of the trajectory. The radio engineering subsystem carried out the correction of the lateral movement of the center of mass and the issuance of a command to turn off the engines, which increased the accuracy characteristics of the rocket. The KVO was 2.5 km when firing at a range of 8500 km.

R-7 carried a monoblock nuclear warhead with a capacity of 5 Mt. Before the launch, the rocket was installed on the launcher. Tanks with kerosene and oxygen were adjusted, and the refueling process began, which lasted almost 2 hours. After passing the start command, the engines of the first and second stages were simultaneously started. Jam-proof radio control commands were transmitted to the rocket from special radio control points.

The missile system turned out to be bulky, vulnerable and very expensive to operate. In addition, the rocket could be in a refueled state for no more than 30 days. An entire plant was needed to create and replenish the necessary supply of liquid oxygen for deployed missiles. It soon became clear that the R-7 and its modifications could not be put on combat duty in large numbers. That's how it all happened. By the time the Caribbean crisis arose, the Soviet Union had only a few dozen of these missiles.

On September 12, 1960, a modified R-7A (8K74) missile was put into service. It had a slightly larger second stage, which made it possible to increase the flight range by 500 km, a lighter warhead and an inertial control system. But, as expected, it was not possible to achieve a noticeable improvement in combat and operational characteristics.

By the mid-60s, both missile systems were decommissioned and the former R-7A ICBM became widely used to launch spacecraft as a launch vehicle. Thus, the spacecraft of the Vostok and Voskhod series were launched into orbit by a three-stage modified modification of the Seven, consisting of six blocks: a central one, four side ones, and a third-stage block. Later, it also became the carrier rocket of the Soyuz spacecraft. Over the long years of space service, various rocket systems have been improved, but no fundamental changes have occurred.

ICBM "Atlas-D" (USA) 1958

ICBM "Atlas-E" (USA) 1962

In 1953, the command of the US Air Force, after conducting another exercise on nuclear bombardment of objects located on the territory of the USSR, and counting the probable losses of its aircraft, finally inclined to the opinion that it was necessary to create ICBMs. The tactical and technical requirements for such a missile were formulated quickly, and at the beginning of the next year, Conver received an order for its development.

In 1957, representatives of the company submitted for testing a simplified version of the ICBM, which received the designation HGM-16 and the name Atlas-A. Eight rockets were built without a warhead and a second-stage engine (it has not yet been brought to full readiness). As shown by the first launches, which ended in explosions and failures, the first stage systems were far from the required standards. And then the news from the Soviet Union about the successful test of an intercontinental missile added fuel "to the fire." state commissions.

A year later, the fully assembled Atlas-V rocket was handed over for testing. Throughout the year, launches were carried out at various ranges. The developers have made significant progress. On November 28, 1958, during the next launch, the rocket flew 9650 km and it became clear to everyone that the Atlas ICBM had taken place. This modification was intended for testing the warhead and methods of combat use. All missile launches of this series were completed successfully (the first - on December 23, 1958). Following the results of the latest tests, a batch of missiles, designated Atlas-D, was ordered for transfer to the SAC units of the Air Force. The very first control launch of ICBMs from this series, which took place on April 14, 1959, ended in an accident. But it was an accident, which was later confirmed.

The work on the rocket did not end there. Two more modifications, E and F, were created and put into service in 1962. There is no reason to call them fundamentally new. The changes affected the equipment of the control system (the radio control system was eliminated), the design of the bow of the rocket body was changed.

The Atlas-F modification was considered the most perfect. She had a mixed design. At launch, all the engines started to work simultaneously, thus representing a single-stage rocket. After reaching a certain speed, the tail section of the hull was separated together with the so-called accelerator engines. The body was assembled from sheet steel. Inside there was a single fuel tank with a length of 18.2 m and a diameter of 3 m. Its internal cavity was divided by a partition into two parts: for oxidizer and fuel. To dampen fuel fluctuations, the inner walls of the tank had a "wafer" design. For the same purpose, after the first accidents, a system of partitions had to be installed. To the lower bottom of the tank on the frame, with the help of explosive bolts, the tail part of the hull (skirt), made of fiberglass, was attached in flight.

ICBM "Atlas-F" (USA) 1962

The propulsion system, which consisted of an LR-105 sustainer engine, two LR-89 launch boosters and two LR-101 steering engines, was located at the bottom of the rocket. All engines were developed in 1954-1958 by Rocketdyne.

The marching rocket engine had an operating time of up to 300 seconds and could develop a thrust of 27.2 tons on the ground. The LR-89 rocket engine developed a thrust of 75 tons, but could only work for 145 seconds. To provide flight control in pitch and roll, its combustion chamber had the ability to deviate by an angle of 5 degrees. Many elements of this engine were identical to the Tor missile rocket engine. In order to simplify the design for the two boosters, the developers provided common elements of the launch system and the gas generator. Exhaust gases from TNA were used to heat helium gas supplied to pressurize the fuel tank. The steering rocket engines had a thrust of 450 kg, an operating time of 360 seconds and could deviate by an angle of 70 degrees.

Kerosene and supercooled liquid oxygen were used as fuel components. The fuel was also used to cool the combustion chambers of the LRE. Powder pressure accumulators were used to launch all three TNAs. The consumption of the components was regulated by a discrete fuel supply control system, special sensors and a calculating device. After the accelerators worked out a given program, they were dropped along with helium cylinders and a skirt.

The rocket was equipped with an inertial-type control system from the Bosch Arma company with a discrete-type computing device and an electronic control device. The memory elements were made on ferrite cores. The flight program, recorded on magnetic tape or magnetic drum, was stored in the rocket shaft. If it became necessary to replace the program, then a new tape or drum was delivered from the missile base by helicopter. The control system provided the QUO of the warhead drop points within a radius of 3.2 km when firing at a range of about 16,000 km.

The head part of the MKZ of a sharp conical shape (on series up to D inclusive, the warhead had a more blunt shape) of the detachable type in flight was stabilized by rotation. Its mass was 1.5 tons. The nuclear monoblock with a capacity of 3–4 Mt had several degrees of protection and reliable detonation sensors. In 1961, a warhead Mk4 weighing 2.8 tons with a more powerful charge was developed, but it was decided to install it on the Titan-1 ICBM.

The Atlas missiles were based in mines with lifting launchers and were ready to launch for about 15 minutes. In total, the Americans deployed 129 launchers with these missiles, and they were in service until the end of 1964.

Even before they were removed from combat duty, Atlases began to be used for space purposes. On February 20, 1962, the Atlas-D rocket launched the Mercury spacecraft with an astronaut on board into orbit. It also served as the first stage of the Atlas-Able three-stage launch vehicle. However, all three launches of this rocket in 1959-1960 from Cape Canaveral ended unsuccessfully. Atlas-F was used to launch satellites for various purposes, including Navstar, into orbit. Subsequently, the Atlases were used as the first stage of the Atlas-Agena, Atlas-Berner-2 and Atlas-Centaurus composite launch vehicles.

But let's go back. In 1955, the US Air Force Strategic Forces Command developed a set of requirements for a heavier missile capable of carrying a powerful thermonuclear warhead. The development task was received by the Martin company. Despite huge efforts, development work on the LGM-25A rocket has clearly dragged on. Only in the summer of 1959, an experimental series of missiles entered flight tests. The first launch, on August 14, was unsuccessful due to a malfunction in the second stage. Subsequent tests were accompanied by numerous failures and accidents. The finishing was difficult. Only on February 2 next year did the long-awaited success come. The test rocket finally took off. It would seem that the black bar is over. But on June 15, in preparation for the launch, an explosion occurred. July 1 had to undermine the rocket in flight due to a large deviation from the desired trajectory. Nevertheless, the efforts of a large team of designers and the financial stimulation of the project yielded positive results, which was confirmed by subsequent launches.

ICBM "Titan-1" (USA) 1961

Start of the ICBM "Titan-1"

On September 29, the Titan-1 rocket (this name was given to the new ICBM by that time) was launched to the maximum range with the equivalent of a 550 kg warhead located in a special experimental building. A rocket launched from the Canaveral range flew 16,000 km and fell into the ocean 1,600 km southeast of about. Madagascar. Separated from the warhead at an altitude of 3 km, a container with instruments was discovered and caught by a search group. In total, for the entire flight test cycle, and it lasted until October 6, 1961, 41 experimental launches of Titan-1 rockets were made, of which 31 were recognized as successful or partially successful.

The two-stage ICBM "Titan-1" is made according to the "tandem" scheme. Each stage had two carrier fuel tanks made of high-strength aluminum alloy. The power set and lining of the tail and instrument compartments were made of magnesium-thorium alloy. Despite its solid size, the dry mass of the rocket did not exceed 9 tons. To decelerate the first stage at the time of separation, the remainder of the oxidizer from the tank was released through two jet nozzles located on the top ring of the tank. At the same time, the main engine of the second stage was turned on.

At the moment of launch on the ground, the LR-87 twin-chamber rocket engine, designed by the Aerojet General Corporation, was turned on, developing a thrust of 136 tons. The fuel supply allowed it to work for 145 seconds. The launch of the TNA, which operated on the main components of the fuel, was carried out with compressed nitrogen. The cooling of the tubular combustion chambers was provided by fuel. The combustion chambers were installed in articulated suspensions, which made it possible to create control forces in flight at the pitch and yaw angles.

Roll control was implemented by installing nozzle nozzles, into which exhaust gases leaving the TNA were supplied.

The second stage is equipped with a single-chamber LRE LR-91, which developed thrust in a vacuum of 36.3 tons. Its operation time is 180 seconds. The combustion chamber was mounted on a gimbal suspension and has a tubular design. Part of the nozzle was cooled. The rest of it was a two-layer packing with an inner layer of asbestos-reinforced phenolic plastic. The exhaust gases after the turbine of the turbopump unit were ejected through a nozzle, which ensured the creation of forces on the roll angle. The fuel for all rocket engines is two-component: fuel - kerosene, oxidizer - liquid oxygen.

The rocket was equipped with an inertial control system with radio correction in the active part of the trajectory using a ground-based computer. It consisted of a tracking radar, a special Athena computer for calculating the actual trajectory, determining the moment the second stage propulsion system was turned off and generating control commands. The inertial device on board the rocket functioned for only two minutes and played a supporting role. The SU provided a firing accuracy of 1.7 km. ICBM "Titan-1" carried detachable in-flight warhead Mk4 with a capacity of 4-7 Mt.

The missile was based in protected silo launchers and had operational readiness for launch in about 15 minutes. The missile system turned out to be very expensive and vulnerable, especially the tracking and control radar. Therefore, the originally planned number of deployable missiles of this type (108) was reduced by 2 times. They were destined for a short life. They were on combat duty for only three years, and at the end of 1964 the last detachment of the Titan-1 ICBM was withdrawn from the SAC.

The abundance of shortcomings and, above all, the low survivability of missile systems with Atlas, Titan-1 and R-7 missiles predetermined their inevitable replacement in the near future. Even during the flight tests of these missiles, it became clear to Soviet and American military specialists that new missile systems needed to be created.

On May 13, 1959, by a special resolution of the Central Committee of the CPSU and the government of the Design Bureau, Academician Yangel was instructed to develop ICBMs on high-boiling fuel components. Subsequently, she received the designation R-16 (8K64). Design teams headed by V. Glushko, V. Kuznetsov, B. Konoplev and others were involved in the development of rocket engines and systems, as well as on the ground and mine launch positions.

ICBM R-16 (USSR) 1961

Initially, the R-16 was supposed to be launched only from ground-based launchers. Extremely tight deadlines were allotted for its design and flight tests.

In the process of preparing the first launch of the rocket on October 23, 1960, after it was refueled with fuel components, a malfunction appeared in the electrical circuit of the automation of the propulsion system, the elimination of which was carried out on a fueled rocket. Since the guarantee of engine performance after filling the turbopump unit with fuel components was determined on the same day, work on preparing for launch and troubleshooting was carried out simultaneously. At the final stage of preparing the rocket for flight, a premature command was sent from the program power distributor to start the second stage engine, as a result of which a fire broke out and the rocket exploded. As a result of the accident, a significant part of the combat crew died, a number of senior officials who were at the starting position near the rocket, including the chief designer of the control system B. M. Konoplev, the chairman of the state commission for testing, the commander-in-chief of the Strategic Missile Forces, Chief Marshal of Artillery M. I. Nedelin. The starting position was disabled by the explosion. The causes of the disaster were studied by a government commission and, based on the results of the investigation, a set of measures was planned and implemented to ensure safety during the development and testing of rocket technology.

ICBM R-16 on parade

The second launch of the R-16 rocket took place on February 2, 1961. Despite the fact that the rocket fell on the flight path due to loss of stability, the developers were convinced that the adopted scheme was viable. After analyzing the results and eliminating the shortcomings, the tests were continued. Hard work made it possible to complete flight tests of the R-16 from ground launchers by the end of 1961, and in the same year to put the first missile regiment on combat duty.

Since May 1960, work has been carried out related to the launch of a modified R-16U (8K64U) missile from a silo launcher. In January 1962, the first launch of a rocket from a silo took place at the Baikonur test site. The following year, a combat missile system with R-16U ICBMs was adopted by the Strategic Missile Forces.

The rocket was made according to the "tandem" scheme with sequential separation of stages. The first, booster stage consisted of a tail section, a fuel tank, an instrument section, an oxidizer tank and an adapter. Tanks of the supporting structure with pressurization in flight: the oxidizer tank was pressurized by the oncoming air flow, and the fuel tank was pressurized by compressed air from cylinders located in the instrument compartment.

The propulsion system consisted of a marching and steering engines. The marching rocket engine is assembled from three identical two-chamber blocks. Each of them included two combustion chambers, a heat pump, a gas generator and a fuel supply system. The total thrust of all blocks on the ground is 227 tons, the operating time is 90 seconds. The steering rocket engine had four rotary combustion chambers with one turbopump unit. The separation of the stages was provided by pyrobolts. Simultaneously with their operation, four brake powder engines located on the first stage were turned on.

The second stage, which served to accelerate the rocket to a speed corresponding to the given flight range, had a similar design as the first, but was made shorter and of a smaller diameter. Both tanks were pressurized with compressed air.

The propulsion system was largely borrowed from the first stage, which reduced the cost and simplified production, but only one block was installed as a sustainer engine. He developed thrust in a vacuum of 90 tons and worked for 125 seconds. The designers managed to successfully solve the problem of reliable launch of the liquid-propellant rocket engine in a rarefied atmosphere, and the sustainer engine was turned on after the detached stage was withdrawn.

Installing the R-16 ICBM on the launch pad

All rocket engines ran on self-igniting fuel components on contact. To refuel the rocket with fuel components, supply it to the combustion chambers, store compressed air and issue it to consumers, the rocket was equipped with a pneumohydraulic system.

The R-16 had a secure autonomous control system. It included a stabilization machine, an RKS system, a SOB, and a range control machine. For the first time on Soviet missiles, a gyro-stabilized platform on a ball-bearing suspension was used as a sensitive element of the control system. The firing accuracy (KVO) was 2.7 km when flying at maximum range. In preparation for the launch, the rocket was mounted on the launcher so that the stabilization plane was in the firing plane. After that, the tanks were filled with fuel components. The R-16 ICBM was equipped with several types of detachable monoblock warhead. The so-called light warhead had a capacity of 3 Mt, and a heavy warhead - 6 Mt.

The R-16 became the base missile for creating a group of intercontinental missiles of the Strategic Missile Forces. The R-16U was deployed in smaller numbers, since the construction of mine complexes took more time than the commissioning of complexes with ground-based launchers. In addition, in 1964 it became clear that this rocket was obsolete. Like all first-generation missiles, these ICBMs could not be fueled for long. In constant readiness, they were stored in shelters or mines with empty tanks, and it took considerable time to prepare for launch. The survivability of missile systems was also low. And yet, for its time, the R-16 was a completely reliable and fairly advanced missile.

Let's go back to 1958 in the USA. And not by chance. The first tests of LRE-equipped ICBMs alarmed the leaders of the missile program about the possibility of completing tests in the near future, and the prospects for such missiles also raised doubts. Under these conditions, attention was paid to solid fuel. As early as 1956, some US industrial firms began active work on the creation of relatively large solid-propellant engines. In this regard, a group of specialists was assembled in the research department of the Rocket Directorate at Raymo-Wooldrige, whose duties were charged with collecting and analyzing data on the progress of research in the field of solid fuel engines. This group was assigned to Colonel Edward Hall, the former head of the Thor missile program, who, as you know, was removed from his post due to a number of test failures of this missile. The active colonel, wanting to rehabilitate himself, after a deep study of the materials, prepared a draft of a new missile system, which promised tempting prospects if implemented. General Shriver liked the project and he asked the management for 150 million dollars for its development. The proposed missile system received the code WS-133A and the name "Minuteman". But the Ministry of the Air Force authorized the allocation of only 50 million to finance the first stage, which provided mainly theoretical research. There is nothing surprising. At that time in the United States, there were many doubters among high-ranking military leaders and politicians about the possibility of the rapid implementation of such a project, which was more based on optimistic ideas that had not yet been tested in practice.

Having been refused full-fledged appropriations, Shriver developed a stormy activity and eventually achieved the allocation in 1959 of a round sum - 184 million dollars. Shriver was not going to take risks with the new rocket, as he had previously, and did everything not to repeat the sad experience. At his insistence, Colonel Otto Glaser, who by that time had proven himself to be a capable organizer, was appointed head of the Minuteman project, who was well connected to the scientific community and influential circles of the military-industrial complex. Such a person was very necessary, since having approved the creation of a new missile system, the leadership of the US Department of Defense set stringent requirements - to enter flight tests at the end of 1960 and ensure that the system was put into service in 1963.

Work unfolded on a broad front. Already in July 1958, the composition of the development companies was approved, and in October the Boeing company was appointed head of assembly, installation and testing. In April-May of the following year, the first full-scale tests of the rocket stages were carried out. To speed up their development, it was decided to involve several companies: Thiokol Chemical Corporation developed the first stage, Aerojet General Corporation - the second stage, Hercules Powder Corporation - the third stage. All stage tests were successfully completed.

In early September of the same year, the Senate declared the Minuteman missile program the highest national priority, which resulted in an additional $899.7 million for its implementation. But despite all the measures, it was not possible to start flight tests at the end of 1960. The first test launch of the Minuteman-1A ICBM took place on February 1, 1961. And immediately good luck. For those times, for American rocket science, this fact was a "fantastic success." There was a big uproar about this. Newspapers touted the Minuteman missile system as the epitome of US technological superiority. The information leak was not accidental. It was used as a means of intimidating the Soviet Union, with which relations with the United States of America sharply worsened, primarily because of Cuba.

However, the reality was not so rosy. Back in 1960, before the start of flight tests, it became clear that the Minuteman-1 A would not be able to fly at a distance of more than 9500 km. Subsequent tests confirmed this assumption. In October 1961, the developers began work on improving the rocket in order to increase the flight range and power of the warhead. Later, this modification received the designation "Minuteman-1B". But they were not going to abandon the deployment of A-series missiles either. At the end of 1962, it was decided to put them on combat duty in the amount of 150 pieces at the Malstrom Air Force Missile Base, Montana.

ICBM "Minuteman-1B" and missile installer

At the beginning of 1963, tests of the Minuteman-1B ICBM were completed, and at the end of this year it began to enter service. By July 1965, the creation of a group of 650 missiles of this type was over. Tests of the Minuteman-1 rocket were carried out at the Western Missile Range (Vandenberg Air Force Base). In total, taking into account combat training launches, 54 missiles of both modifications were launched.

For its time, the LGM-30A Minuteman-1 ICBM was very advanced. And what is very important, she had, as the representative of the Boeing company said, "... unlimited opportunities for improvement." This was not empty bravado, and the reader will be able to verify this below. Three-stage, with sequential separation of stages, the rocket was made of modern materials for that time.

The first stage engine housing was made of special steel with high purity and strength. A coating was applied to its inner surface, which ensured the connection of the body with the fuel charge. It also served as a thermal protection, which made it possible to compensate for the change in the volume of fuel with fluctuations in the temperature of the charge. Solid propellant rocket engine M-55 had four rotary nozzles. Developed traction on the ground at 76 tons. Its operation time is 60 seconds. Mixed fuel, consisting of ammonium perchlorate, polybutadiene copolymer, acrylic acid, epoxy resin and aluminum powder. Filling the charge into the case was controlled by a special computer.

ICBM R-9A (USSR) 1965

The second stage engine had a titanium alloy body. A charge of mixed propellant based on polyurethane was poured into the hull. A similar stage of the Minuteman-1B rocket had a charge of a slightly larger mass. Four rotary nozzles provided flight control. The solid propellant rocket engine M-56 developed traction in a vacuum of 27 tons.

The third stage engine had a fiberglass casing. He developed a thrust of 18.7 tons. The duration of his work was about 65 seconds. The composition of the fuel charge was similar to that of the solid propellant rocket engine of the second stage. Four swivel nozzles provided control to all angles.

The inertial control system, built on the basis of a sequential type computer, provided control of the missile's flight in the active part of the trajectory and a firing accuracy (KVO) of 1.6 km. The Minuteman-1 A carried a 0.5 Mt Mk5 monoblock nuclear warhead, which was aimed at a predetermined target. "Minuteman-1 V" was equipped with a monoblock nuclear warhead Mk11 with a capacity of 1 Mt. Before launch, it could be aimed at one of two possible targets of destruction. The missiles were stored in silo launchers and could be launched a minute after the launch command was received from the detachment's command post. The main engine of the first stage was launched directly in the mine, and in order to reduce the heating of the hull by hot gases, it was covered on the outside with a special protective paint.

The presence of such a missile system in service significantly increased the potential of the US nuclear forces, and also created the conditions for delivering a surprise nuclear strike against the enemy. Its appearance caused great concern among the Soviet leadership, since the R-16 ICBM, for all its merits, was clearly inferior to the American missile in terms of survivability and combat readiness, and the R-9A (8K75) ICBM being developed at OKB-1 had not yet passed flight tests. It was created in accordance with a government decree of May 13, 1959, although some work on the design of such a rocket began much earlier.

The beginning of flight design tests of the R-9 (S.P. Korolev was present at the first launch on April 9, 1961) cannot be called completely successful. The lack of knowledge of the LRE of the first stage affected - strong pressure pulsations in the combustion chamber summed it up. He was put on a rocket under pressure from V. Glushko. Although it was decided to create propulsion systems for this rocket on a competitive basis, the head of the GDL-OKB could not drop the prestige of his team, which was considered the leader in engine building.

This was the cause of the explosions during the first launches. Design teams led by A. Isaev and N. Kuznetsov also took part in the competition. The design bureau of the latter, as a result of the curtailment of the program for the construction of engines for aircraft, was left with practically no orders. The Kuznetsov LRE was built according to a more advanced closed circuit with afterburning of exhaust turbogas in the main combustion chamber. In the LRE Glushko and Isaev, created according to an open scheme, the gas exhausted in the turbopump unit was discharged through the exhaust pipe into the atmosphere. The works of all three design bureaus reached the stage of bench tests, but the competitive selection did not work out. The “lobbyist” approach of OKB Glushko still took the upper hand.

In the end, the problems in the engines were eliminated. However, the tests were delayed, since the original method of launching from a ground-based launcher was abandoned in favor of the mine version. Simultaneously with the increase in the reliability of the rocket, OKB-1 specialists had to solve a problem on which the very possibility of finding the "nine" on combat duty depended. We are talking about methods for long-term storage of large quantities of liquid oxygen for refueling rocket tanks. As a result, a system was created that ensured oxygen losses of no more than 2–3% per year.

Flight tests were completed in February 1964, and on July 21, 1965, the rocket under the R-9A index was put into service and was on combat duty until the second half of the 70s.

Structurally, the R-9A was divided into the first stage, which consisted of a tail section of the propulsion system with nozzle fairings and short stabilizers, cylindrical fuel and oxidizer fuel tanks and a truss adapter. Instruments of the control system were “embedded” into the shell of the inter-tank compartment.

The "Nine" was distinguished by a relatively short section of the first stage, as a result of which the separation of the stages took place at a height where the influence of the velocity pressure on the rocket is still significant. The so-called "hot" method of stage separation was implemented on the rocket, in which the second stage engine was started at the end of the first stage sustainer engine. In this case, hot gases flow through the truss structure of the adapter. Due to the fact that at the time of separation of the LRE the second stage was operating at only 50% of the rated thrust and the short second stage was aerodynamically unstable, the steering nozzles could not cope with the disturbing moments. To eliminate this shortcoming, the designers installed special aerodynamic shields on the outer surface of the tail section to be dropped, the opening of which, when the stages were separated, shifted the center of pressure and increased the stability of the rocket. After the rocket engine entered the operating mode of thrust, the fairing of the tail compartment, together with these shields, was dropped.

ICBM R-9A (USSR) 1965

With the advent of the United States systems for detecting ICBM launches using a powerful engine torch, the short section of the first stage became the advantage of the "nine". After all, the shorter the torch's lifetime, the more difficult it is for missile defense systems to respond to such a missile. On the R-9A engines were installed on oxygen-kerosene fuel. S. Korolev paid special attention to such fuel as non-toxic, high-energy and cheap to produce.

At the first stage there was a four-chamber RD-111 with the exhaust of spent steam and gas from the HP through a fixed nozzle between the chambers. To provide control of the rocket, the cameras were made swinging. The engine developed a thrust of 141 tons and worked for 105 seconds.

A four-chamber liquid-propellant rocket engine with steering nozzles RD-461 designed by S. Kosberg was installed at the second stage. He had a record specific impulse for that time among oxygen-kerosene engines and developed thrust in a vacuum of 31 tons. The maximum operating time was 165 seconds. To quickly bring the propulsion systems to the nominal mode and ignite the fuel components, a special launch system with pyro-igniters was used.

A combined control system was installed on the rocket, which ensured firing accuracy (KVO) at ranges over 12,000 km, not more than 1.6 km. On the R-9A, the radio channel was eventually abandoned.

For the R-9A ICBM, two variants of single-block nuclear warheads were developed: standard and heavy, weighing 2.2 tons. The first had a capacity of 3 Mt and could be delivered to a distance of over 13,500 km, the second - 4 Mt. With it, the range of the missile reached 12,500 km.

As a result of the introduction of a number of technical innovations, the rocket turned out to be compact, suitable for launching both from ground and silo launchers. The rocket, launched from a ground launcher, additionally had a transition frame, which was attached to the tail compartment of the first stage.

Despite its merits, by the time the first missile regiment was placed on combat duty, the "nine" no longer fully met the set of requirements for combat strategic missiles. And not surprising, since it belonged to the first generation of ICBMs and retained their inherent features. Surpassing the American Titan-1 ICBM in combat, technical and operational characteristics, it was inferior to the latest Minutemen in terms of firing accuracy and launch preparation time, and these indicators became decisive by the end of the 60s. R-9A became the last combat missile on oxygen-kerosene fuel.

The rapid development of electronics in the early 60s opened up new horizons for the development of military systems for various purposes. For rocket science, this factor was of great importance. It became possible to create more advanced missile control systems capable of ensuring high hit accuracy, to a large extent automate the operation of missile systems, and most importantly, automate centralized combat control systems that can ensure guaranteed delivery of launch orders to ICBMs coming only from the high command (president) and prevent the unauthorized use of nuclear weapons.

The Americans were the first to start this work. They did not need to create a completely new rocket. Even during the work on the Titan-1 rocket, it became clear that its characteristics could be improved by introducing new technologies into production. At the beginning of 1960, the designers of the Martin company set about modernizing the rocket, and at the same time creating a new launch complex.

The flight design tests that began in March 1962 confirmed the correctness of the chosen technical strategy. In many ways, the rapid progress of work was facilitated by the fact that the new ICBM inherited a lot from its predecessor. In June of the following year, the Titan-2 missile was adopted by the strategic nuclear forces, although control and combat training launches were still ongoing. In total, from the beginning of testing to April 1964, 30 launches of this type of missiles at various ranges were carried out from the Western Missile Range. Rocket "Titan-2" was intended to destroy the most important strategic targets. Initially, it was planned to put 108 units on duty, replacing all of the Titan-1. But plans changed, and as a result they were limited to 54 missiles.

Despite being closely related, the Titan-2 ICBM had many differences from its predecessor. The way fuel tanks are pressurized has changed. The oxidizer tank at the first stage was pressurized with gaseous nitrogen tetroxide, the fuel tanks of both stages were pressurized with cooled generator gas, the second stage oxidizer tank was not pressurized at all. During operation of the engine of this stage, thrust constancy was ensured by maintaining a constant ratio of fuel components in the gas generator using Venturi nozzles installed in the fuel supply lines. The fuel has also been changed. Stable aerozine-50 and nitrogen tetroxide were used to power all rocket engines.

ICBM "Titan-2" in flight

ICBM "Minuteman-2" in the silo

At the first stage, a modernized two-chamber rocket engine LR-87 with a thrust on the ground of 195 tons was installed. Its turbopump unit was spun with a powder starter. The mid-flight rocket engine of the second stage LR-91 has also undergone modernization. Increased not only its thrust (up to 46 tons), but also the degree of expansion of the nozzle. In addition, two steering solid propellant rocket engines were installed in the tail section.

On the rocket, fire separation of the steps was used. The main engine of the second stage was switched on when the pressure in the combustion chambers of the rocket engine dropped to 0.75 nominal, which gave the effect of braking. At the moment of separation, two brake engines were turned on. When separating the warhead from the second stage, the latter was decelerated by three brake solid propellant rocket motors and taken away.

The flight of the rocket was controlled by an inertial control system with a small-sized GPS and digital computer, which performed 6000 operations per second. A lightweight magnetic drum with a capacity of 100,000 units of information was used as a storage device, which made it possible to store several flight tasks for one rocket in memory. The control system provided a firing accuracy (KVO) of 1.5 km and automatic conduct, on command from the control center, of the pre-launch preparation and missile launch cycle.

Due to the increase in throwable weight, the Titan-2 was equipped with a heavier monoblock warhead Mkb with a capacity of 10–15 Mt. In addition, she carried a set of passive means of overcoming missile defense.

Due to the placement of ICBMs in single silo launchers, it was possible to significantly increase their survivability. Since the rocket was in the mine in a refueled state, the operational readiness for launch increased. It took a little over a minute for the rocket, after receiving the order, to rush to the chosen target.

Before the advent of the Soviet R-36 missile, the Titan-2 intercontinental ballistic missile was the most powerful in the world. She was on combat duty until 1987. The modified Titan-2 rocket was also used for peaceful purposes to launch various spacecraft into orbit, including the Gemini spacecraft. On its basis, various versions of the Titan-3 launch vehicles were created.

The Minuteman missile system also received its further development. This decision was preceded by the work of a special Senate commission, whose task was to determine the further and, if possible, more economical way for the development of strategic weapons for the United States. The conclusions of the commission indicated that it was necessary to develop the ground component of the American strategic nuclear forces based on the Minuteman missile.

ICBM "Titan-2" (USA) 1963

In July 1962, Boeing received an order to develop the LGM-30F Minuteman 2 rocket. To meet the requirements of the customer, the designers needed to create a new second stage and control system. But the missile system is not only a rocket. It was necessary to significantly modernize ground technological and technical equipment, command post systems and launchers. At the end of the summer of 1964, the new ICBM was ready for flight tests. On September 24, the first launch of the Minuteman-2 ICBM was carried out from the Western Missile Range. The entire set of tests was completed in a year, and in December 1965, the deployment of these missiles began at Grand Forks Air Force Base, North Dakota. In total, taking into account combat training launches conducted by regular crews to gain experience in combat use, for the period from September 1964 to the end of 1967, 46 launches of ICBMs of this type took place from the Vandenberg base.

On the Minuteman 2 rocket, the first and third stages did not differ from those of the Minuteman 1 B rocket, but the second was completely new. Aerojet General Corporation has developed the SR-19 solid propellant rocket engine with a vacuum thrust of 27 tons and an operating time of up to 65 seconds. The engine housing was made of titanium alloy. The use of fuel based on polybutadiene made it possible to obtain a higher specific impulse. To achieve the specified firing range, it was necessary to increase the fuel supply by 1.5 tons. Since the rocket engine now had only one fixed nozzle, the designers had to develop new ways to generate control forces.

The pitch and yaw angles were controlled by controlling the thrust vector by injecting freon into the supercritical part of the solid propellant rocket engine nozzle through four holes located along the circumference at an equal distance from each other. The control forces on the angle of roll were implemented by four small jet nozzles that were built into the engine case. Their functioning was provided by a powder pressure accumulator. Freon stock was stored in a toroidal tank, put on the top of the nozzle.

The rocket was equipped with an inertial control system with a universal digital computing device assembled on microcircuits. All gyroscopes of the GSP sensitive elements were in the untwisted state, which made it possible to maintain the rocket in a very high readiness for launch. The excess heat released in this case was removed by a thermostating system. Gyroblocks could operate in this mode continuously for 1.5 years, after which they had to be replaced. A storage device on a magnetic disk provided storage of eight flight tasks calculated for various objects of destruction.

When the missile was on combat duty, its control system was used to carry out checks, calibrate on-board equipment and other tasks that were solved in the process of maintaining combat readiness. When firing at maximum range, it provided a firing accuracy (KVO) of 0.9 km.

"Minuteman-2" was equipped with a monoblock nuclear warhead Mk11 of two modifications, differing in charge power (2 and 4 Mt). The rocket managed to place the means of overcoming missile defense.

By the beginning of 1971, the entire group of Minuteman-2 ICBMs was fully deployed. It was originally planned to supply the Air Force with 1,000 missiles of this type (upgrading 800 Minuteman-1A (B) missiles and building 200 new ones). But the military department had to reduce requests. As a result, only half (200 new and 300 modernized) missiles were put on combat duty.

After the Minuteman-2 missiles were installed in the launch silos, the very first checks revealed failures of the onboard control system. The flow of such failures increased markedly and the only repair base in the city of Newark could not cope with the volume of repairs due to limited production capacity. For these purposes, the capacity of the manufacturer of the Otonetics company had to be used, which immediately affected the pace of production of new missiles. The situation became even more complicated when the modernization of the Minuteman-1B ICBM began at the missile bases. The reason for this unpleasant phenomenon for the Americans, which also led to a delay in the deployment of the entire group of missiles, was that even at the stage of developing tactical and technical requirements, an insufficient level of reliability of the control system was laid down. Requests for repairs were dealt with only by October 1967, which of course required additional cash costs.

At the beginning of 1993, the US strategic nuclear forces had 450 deployed Minuteman-2 ICBMs and about 50 missiles in reserve. Naturally, over the long period of operation, the missile was modernized in order to increase its combat capabilities. The improvement of some elements of the control system made it possible to increase the accuracy of fire to 600 m. The fuel charges were replaced in the first and third stages. The need for such work was caused by the aging of the fuel, which affected the reliability of the missiles. Increased protection of launchers and command posts of missile systems.

Over time, such an advantage as a long service life has turned into a disadvantage. The thing is that the established cooperation of firms engaged in the production of missiles and components for them at the stage of development and deployment began to disintegrate. Periodic updating of various missile systems required the manufacture of products that had not been produced for a long time, and the costs of maintaining a group of missiles in a combat-ready state were steadily increasing.

In the USSR, the UR-100 missile, developed under the guidance of Academician Vladimir Nikolaevich Chelomey, became the first second-generation ICBM to be equipped with the Strategic Missile Forces. The task was issued to the team headed by him on March 30, 1963 by the relevant government decree. In addition to the head design bureau, a significant number of related organizations were involved, which made it possible to work out all the systems of the missile complex being created in a short time. In the spring of 1965, flight tests of the rocket began at the Baikonur test site. On April 19, a launch took place from a ground-based launcher, and on July 17, the first launch from a mine. The first tests showed the lack of knowledge of the propulsion system and control system. However, the elimination of these shortcomings did not take long. On October 27 of the following year, the entire flight test program was fully completed. On November 24, 1966, the combat missile system with the UR-100 missile was adopted by the missile regiments.

ICBM UR-100 was made according to the "tandem" scheme with sequential separation of stages. The fuel tanks of the supporting structure had a combined bottom. The first stage consisted of the tail section, propulsion system, fuel and oxidizer tanks. The propulsion system included four sustainer liquid-propellant rocket engines with rotary combustion chambers, made according to a closed circuit. The engines had a high specific thrust impulse, which made it possible to limit the operating time of the first stage.

ICBM PC-10 (USSR) 1971

The second stage is similar in design to the first, but smaller. Its propulsion system consisted of two liquid-propellant rocket engines: a single-chamber sustainer and a four-chamber steering.

To increase the energy capabilities of the engines, to ensure refueling and draining of rocket fuel components, the rocket had a pneumohydraulic system. Its elements were placed on both steps. Nitrogen tetroxide and asymmetric dimethylhydrazine, self-igniting upon mutual contact, were used as fuel components.

An inertial control system was installed on the rocket, which ensured a firing accuracy (KVO) of 1.4 km. Its component subsystems were distributed throughout the rocket. The UR-100 carried a single-block warhead with a nuclear charge of 1 Mt, separated in flight from the second stage.

The great advantage was that the rocket was ampouled (isolated from the external environment) in a special container in which it was transported and stored in the silo launcher for several years in constant readiness for launch. The use of membrane valves separating fuel tanks with aggressive components from rocket engines made it possible to keep the rocket constantly refueled. The rocket was launched directly from the container. Monitoring the technical condition of missiles of one combat missile system, as well as pre-launch preparation and launch, were carried out remotely from a single command post.

The UR-100 ICBM was further developed in a number of modifications. In 1970, the UR-100 UTTKh missiles, which had a more advanced control system, a more reliable warhead and a set of means to overcome anti-missile defense, began to enter service.

Even earlier, on July 23, 1969, flight tests of another modification of this missile, which received the military designation UR-100K (RS-10), began at the Baikonur training ground. They ended on March 15, 1971, after which the replacement of the UR-100 missiles began.

The new missile surpassed its predecessors in terms of firing accuracy, reliability and performance. The propulsion systems of both stages were modified. The service life of LRE has been increased, as well as their reliability. A new transport and launch container was developed. Its design has become more rational and convenient, which made it possible to facilitate the maintenance of the rocket and reduce the maintenance time by three times. The installation of new control equipment made it possible to fully automate the cycle of checking the technical condition of missiles and launcher systems. The security of the missile complex facilities has been increased.

ICBM UR-100 in TPK on parade

PC-10 ICBM assembly without warhead (outside the launch canister)

For the beginning of the 70s, the rocket had high combat characteristics and reliability. The flight range was 12,000 km, the accuracy of delivery of a monoblock warhead of the megaton class was 900 m. All this determined its long service life, which was repeatedly extended by the commission of the chief designer: the combat missile system with the UR-100K missile adopted by the Strategic Missile Forces in October 1971 was on the combat on duty until 1994. In addition, the PC-10 family has become the most massive of all Soviet ICBMs.

On June 16, 1971, the last modification of this family, the UR-100U rocket, launched on its first flight from Baikonur. It was equipped with a warhead with three dispersing warheads. Each block carried a nuclear charge with a capacity of 350 kt. During the tests, a flight range of 10,500 km was achieved. At the end of 1973, this ICBM entered service.

The next ICBM of the second generation, which entered the equipment of the Strategic Missile Forces, was the R-36 (8K67) - the ancestor of Soviet heavy missiles. By a government decree of May 12, 1962, Academician Yangel's Design Bureau was instructed to create a rocket capable of significantly supporting N. S. Khrushchev's ambitions. It was intended to destroy the most important strategic objects of the enemy, protected by missile defense systems. The terms of reference provided for the creation of a rocket in two versions, which should have differed in the methods of basing: with a ground launch (like the American Atlas) and with a mine launch, like the R-16U. The unpromising first option was quickly abandoned. And yet, the rocket was developed in two versions. But now they differed in the principle of building a control system. The first rocket had a purely inertial system, and the second - an inertial system with radio correction. When creating the complex, special attention was paid to the maximum simplification of the launch positions, which were developed by the design bureau under the leadership of E. G. Rudyak: their reliability was increased, rocket refueling was excluded from the launch cycle, remote control of the main parameters of the rocket and systems was introduced in the process of combat duty, preparation for launch and remote missile launch.

ICBM R-36 (USSR) 1967

1 - the upper part of the cable box; 2 - second stage oxidizer tank; 3 - fuel tank of the second stage; 4 - pressure sensor of the traction control system; 5 - frame for fastening engines to the body; 6 - turbopump unit; 7 - LRE nozzle; 8 - steering rocket engine of the second stage; 9 - brake powder engine of the first stage; 10 - protective fairing of the steering motor; 11 - intake device; 12 - first stage oxidizer tank; 13 - block of the missile control system, located on the first stage; 14 - fuel tank of the first stage; 15 - protected oxidant supply pipeline; 16 - fixing the frame of the rocket engine to the body of the tail compartment of the first stage; 17 - LRE combustion chamber; 18 - steering engine of the first stage; 19 - drainage pipe; 20 - pressure sensor in the fuel tank; 21 - pressure sensor in the oxidizer tank.

ICBM R-36 on parade

The tests were carried out at the Baikonur test site. On September 28, 1963, the first launch took place, which ended unsuccessfully. Despite the initial failures and failures, members of the state commission under the leadership of Lieutenant General M.G. Grigoriev recognized the missile as promising and had no doubts about its ultimate success. The system of testing and development of the missile system adopted by that time made it possible, simultaneously with flight tests, to launch mass production of missiles, technological equipment, as well as the construction of launch sites. At the end of May 1966, the entire test cycle was completed, and on July 21 of the following year, the DBK with R-36 ICBMs was put into service.

The two-stage R-36 is made according to the "tandem" scheme of high-strength aluminum alloys. The first stage provided rocket acceleration and consisted of a tail section, a propulsion system, and fuel and oxidizer fuel tanks. The fuel tanks were pressurized in flight by the products of combustion of the main components and had devices for damping vibrations.

The propulsion system consisted of a six-chamber marching and four-chamber steering liquid rocket engines. The marching rocket engine was assembled from three identical two-chamber blocks mounted on a common frame. The supply of fuel components to the combustion chambers was provided by three HPs, the turbines of which were spun by the products of fuel combustion in the gas generator. The total thrust of the engine near the ground was 274 tons. The steering rocket engine had four rotary combustion chambers with one common turbopump unit. The cameras were installed in the "pockets" of the tail compartment.

The second stage provided acceleration to a speed corresponding to a given firing range. Her fuel tanks of the supporting structure had a combined bottom. The propulsion system located in the tail compartment consisted of a two-chamber marching and a four-chamber steering liquid-propellant rocket engines. The RD-219 sustainer liquid-propellant rocket engine is in many respects similar in design to the first-stage propulsion units. The main difference was that the combustion chambers were designed for a large degree of expansion of the gas and their nozzles also had a large degree of expansion. The engine consisted of two combustion chambers, a TNA feeding them, a gas generator, automation units, an engine frame and other elements. He developed thrust in a vacuum of 101 tons and could work for 125 seconds. The steering engine did not differ in design from the engine installed in the first stage.

ICBM R-36 at launch

All LRE rockets were developed by GDL-OKB designers. For their power, a two-component fuel self-igniting on contact was used: the oxidizer was a mixture of nitrogen oxides with nitric acid, the fuel was unsymmetrical dimethylhydrazine. For refueling, draining and supplying fuel components to rocket engines, a pneumohydraulic system was installed on the rocket.

The steps were separated from each other and the head part by actuating explosive bolts. To avoid collisions, braking of the separated stage was provided due to the operation of brake powder engines.

For R-36 developed a combined control system. The autonomous inertial system provided control on the active part of the trajectory and included a stabilization machine, a range machine, a SSS system that provides simultaneous production of oxidizer and fuel from tanks, and a system for turning the rocket after launch to the designated target. The radio control system was supposed to correct the movement of the rocket at the end of the active site. However, during flight tests, it became clear that the autonomous system provides the specified firing accuracy (KVO about 1200 m) and the radio system was abandoned. This made it possible to significantly reduce financial costs and simplify the operation of the missile system.

The R-36 ICBM was equipped with a monoblock thermonuclear warhead of one of two types: light - with a capacity of 18 Mt and heavy - with a capacity of 25 Mt. To overcome the enemy's anti-missile defense, a reliable set of special means was installed on the rocket. In addition, there was a system for the emergency destruction of a warhead, which was triggered when the movement parameters on the active section of the trajectory deviated beyond the permissible limits.

The rocket was launched automatically from a single silo, where it was stored in a refueled state for 5 years. A long service life was achieved by sealing the rocket and creating an optimal temperature and humidity regime in the mine. The DBK with the R-36 possessed unique combat capabilities and significantly surpassed the American complex of a similar purpose with the Titan-2 missile, primarily in terms of nuclear charge power, firing accuracy and security.

The last of the Soviet missiles of this period, which entered service, was the combat solid-fuel ICBM PC-12. But long before that, in 1959, in the design bureau headed by S.P. Korolev, the development of an experimental rocket with solid fuel engines, designed to destroy objects at medium ranges, began. Based on the test results of the units and systems of this rocket, the designers concluded that it is possible to create an intercontinental rocket. A discussion ensued between supporters and opponents of this project. At that time, the Soviet technology for creating large mixed charges was just in its infancy, and naturally there were doubts about the ultimate success. Everything was too new. The decision to create a solid-propellant rocket was made at the very "top". Not the last role was played by news from the United States about the start of testing ICBMs on mixed solid fuel. On April 4, 1961, a government decree was issued, in which the Korolev design bureau was appointed as the head of the creation of a fundamentally new stationary-type combat missile system with a solid-fuel intercontinental missile equipped with a monoblock warhead. Many research organizations and design bureaus were involved in solving this problem. On January 2, 1963, a new test site, Plesetsk, was created to test intercontinental missiles and implement a number of other programs.

In the process of developing the missile complex, complex scientific, technical and production problems had to be solved. So, mixed solid fuels, large-sized engine charges were developed and the technology for their manufacture was mastered. A fundamentally new control system has been created. A new type of launcher was developed, which ensures the launch of a rocket on a sustainer engine from a blank launcher.

RS-12, second and third stages without warhead

ICBM PC-12 (USSR) 1968

The first launch of the RT-2P rocket took place on November 4, 1966. The tests were carried out at the Plesetsk test site under the leadership of the state commission. It took exactly two years to completely dispel all the doubts of skeptics. On December 18, 1968, the missile system with this missile was adopted by the Strategic Missile Forces.

The RT-2P rocket had three stages. To connect them to each other, connecting compartments of the truss structure were used, which allowed the gases of the sustainer engines to freely escape. The engines of the second and third stages were switched on a few seconds before the pyrobolts were activated.

Rocket engines of the first and second stages had steel housings and nozzle blocks, consisting of four split control nozzles. The rocket engine of the third stage differed from them in that it had a body of mixed design. All engines were made in different diameters. This was done in order to provide a given flight range. To launch the solid propellant rocket engine, special igniters were used, mounted on the front bottoms of the hulls.

The missile control system is autonomous inertial. It consisted of a set of instruments and devices that controlled the movement of the rocket in flight from the moment of launch to the transition to uncontrolled flight of the warhead. Calculators and pendulum accelerometers were used in the control system. Control system elements were located in the instrument compartment installed between the head and the third stage, and its executive bodies - at all stages in the tail compartments. The firing accuracy was 1.9 km.

The ICBM carried a monoblock nuclear charge with a capacity of 0.6 Mt. Monitoring the technical condition and launching of missiles was carried out remotely from the command post of the DBK. The important features of this complex for the troops were ease of operation, a relatively small number of service units and the lack of refueling facilities.

The appearance of missile defense systems among the Americans required the modernization of the missile in relation to the new conditions. Work began in 1968. On January 16, 1970, the first test launch of the modernized rocket took place at the Plesetsk test site. Two years later, she was adopted.

The modernized RT-2P differed from its predecessor by a more advanced control system, a warhead, the nuclear charge power of which was increased to 750 kt, and improved operational characteristics. Firing accuracy increased to 1.5 km. The missile was equipped with a complex to overcome missile defense systems. The upgraded RT-2P and the previously fired missiles, which were delivered to the missile units in 1974 and modified to their technical level, were on combat duty until the mid-1990s.

By the end of the 1960s, conditions began to emerge for achieving nuclear parity between the United States and the Soviet Union. The latter, rapidly building up the combat potential of its strategic nuclear forces and, above all, the Strategic Missile Forces, in the coming years could catch up with the United States of America in terms of the number of nuclear charge carriers. Overseas, such a prospect of high-ranking politicians and military did not please.

RS-12, first stage

The next round of the missile arms race was associated with the creation of multiple reentry vehicles with individually targetable warheads (MIRV-type MIRVs). Their appearance was caused, on the one hand, by the desire to have as many nuclear charges as possible to hit targets, and, on the other hand, by the inability to infinitely increase the number of launch vehicles for a number of economic and technical reasons.

A higher level of development of science and technology at that time allowed the Americans to be the first to start work on the creation of MIRVs. Initially, dispersing warheads were developed in a special scientific center. But they were only suitable for hitting area targets due to the low pointing accuracy. Such a MIRV was equipped with the Polaris-AZT SLBM. The introduction of powerful on-board computers made it possible to increase the accuracy of guidance. At the end of the 60s, the specialists of the scientific center completed the development of the Mk12 and Mk17 individual guidance MIRVs. Their successful tests at the White Sands army test site (all American warheads with a nuclear charge were tested there) confirmed the possibility of their use on ballistic missiles.

The Mk12 carrier, the design of which was developed by representatives of the General Electric company, was the Minuteman-3 ICBM, which Boeing began designing at the end of 1966. Possessing high firing accuracy, according to the plan of American strategists, it was supposed to become a "thunderstorm of Soviet missiles." Based on the previous model. Significant alterations were not required, and in August 1968 the new missile was transferred to the Western Missile Range. There, according to the program of flight design tests for the period from 1968 to 1970, 25 launches were carried out, of which only six were recognized as unsuccessful. After the completion of this series, six more demonstration launches were carried out for high authorities and ever-doubting politicians. All of them were successful. But they were not the last in the history of this ICBM. During its long service, 201 launches were carried out both for testing and training purposes. The rocket showed high reliability. Only 14 of them failed (7% of the total).

Since the end of 1970, the Minuteman-3 began to enter service with the SAC of the US Air Force to replace all the remaining Minuteman-1B missiles and 50 Minuteman-2 missiles at that time.

ICBM "Minuteman-3" structurally consists of three successive marching solid propellant rocket motors and docked to the third stage MIRV with a fairing. Engines of the first and second stages - M-55A1 and SR-19, inherited from their predecessors. The SR-73 solid propellant rocket engine was designed by United Technologies specifically for the third stage of this rocket. It has a bonded solid propellant charge and one fixed nozzle. During its operation, the control in pitch and yaw angles is carried out by injecting liquid into the supercritical part of the nozzle, and in roll, using an autonomous gas generator system installed on the hull skirt.

The new NS-20 brand control system was developed by Rockwell International's Otonetics division. It is intended for flight control on the active part of the trajectory; calculation of the trajectory parameters in accordance with the flight task recorded in the memory devices of the three-channel onboard computer; calculation of control commands for actuator actuators of the rocket; management of the warhead disengagement program when aiming them at individual targets; implementation of self-control and control of the functioning of on-board and ground systems in the process of combat duty and pre-launch preparation. The main part of the equipment is placed in a sealed instrument compartment. The GSP gyroblocks are in the untwisted state when on combat duty. The released heat is removed by the temperature control system. SU provides shooting accuracy (KVO) of 400 m.

ICBM "Minuteman-3" (USA) 1970

I - the first stage; II - the second step; III - the third stage; IV - head part; V - connecting compartment; 1 - combat unit; 2 - platform of warheads; 3 - electronic blocks of automation of warheads; 4 - starting device solid propellant rocket motor; 5 - charge of solid rocket engine fuel; 6 - thermal insulation of the rocket engine; 7 - cable box; 8 - device for blowing gas into the nozzle; 9 - solid propellant nozzle; 10 - connecting skirt; 11 - tail skirt.

We will focus on the design of the Mk12 head part. Structurally, the MIRV consists of a combat compartment and a breeding stage. In addition, a complex of means of overcoming missile defense can be installed, in which chaff is used. The mass of the head part with a fairing is a little more than 1000 kg. The fairing originally had an ogive shape, then a triconic one and was made of a titanium alloy. The warhead body is two-layer: the outer layer is a heat-shielding coating, the inner one is a power shell. A special tip is installed at the top.

At the bottom of the dilution stage is the propulsion system, which includes an axial thrust engine, 10 orientation and stabilization engines, and two fuel tanks. Two-component liquid fuel is used to power the propulsion system. The displacement of components from the tanks is carried out by the pressure of compressed helium, the supply of which is stored in a spherical cylinder. The thrust of the axial thrust engine is 143 kg. The duration of the remote control is about 400 seconds. The power of the nuclear charge of each warhead is 330 kt.

In a relatively short time, a group of 550 Minuteman-3 missiles was deployed at four missile bases. The missiles are in the silo in 30-second readiness for launch. The launch was carried out directly from the shaft after the first stage solid propellant rocket engine entered the operating mode.

All Minuteman-3 missiles have been upgraded more than once. The charges of rocket engines of the first and second stages were replaced. The characteristics of the control system were improved by taking into account the errors of the complex of command instruments and the development of new algorithms. As a result, the firing accuracy (KVO) was 210 m. In 1971, a program began to improve the security of silo launchers. It provided for the strengthening of the structure of the mine, the installation of a new missile suspension system and a number of other measures. All work was completed in February 1980. The security of the silo has been brought to a value of 60–70 kg/cm?.

ICBM RS-20A with MIRV (USSR) 1975

1 - the first stage; 2 - second stage; 3 - connecting compartment; 4 - head fairing; 5 - tail section; 6 - carrier tank of the first stage; 7 - combat unit; 8 - propulsion system of the first stage; 9 - frame for fastening the propulsion system; 10 - fuel tank of the first stage; 11 - mains of the ASG of the first stage; 12 - oxidizer supply pipeline; 13 - first stage oxidizer tank; 14 - power element of the connecting compartment; 15 - steering rocket engine; 16 - propulsion system of the second stage; 17 - fuel tank of the second stage; 18 - second stage oxidizer tank; 19 - highway ASG; 20 - control system equipment.

On August 30, 1979, a series of 10 flight tests was completed to test the improved Mk12A MIRV. It was installed instead of the previous one on 300 Minuteman-3 missiles. The charge power of each warhead was increased to 0.5 Mt. True, the area for breeding blocks and the maximum flight range have somewhat decreased. In general, this ICBM is reliable and capable of hitting targets throughout the former Soviet Union. Experts believe that she will be on alert until the beginning of the next millennium.

The appearance of MIRVed missiles in service with the US strategic nuclear forces sharply worsened the position of the USSR. Soviet ICBMs immediately fell into the category of morally obsolete, since they could not solve a number of newly emerging tasks, and most importantly, the probability of delivering an effective retaliatory strike was significantly reduced. There was no doubt that the warheads of the Minuteman-3 missiles, in the event of a nuclear war, would strike at silo launchers and command posts of the Strategic Missile Forces. And the likelihood of such a war at that time was very high. In addition, in the second half of the 60s, work in the field of missile defense intensified in the United States.

The problem could not be solved by only creating a new ICBM. It was necessary to improve the system of combat control of missile weapons, increase the protection of command posts and launchers, and also solve a number of additional tasks. After a detailed study by specialists of options for the development of the Strategic Missile Forces and a report on the results of research to the leadership of the state, it was decided to develop heavy and medium-sized missiles capable of carrying a significant payload and ensuring parity in the field of nuclear weapons. But this meant that the Soviet Union was being drawn into a new round of the arms race, and in the most dangerous and costly area at that.

The Dnepropetrovsk Design Bureau, which after the death of M. Yangel was headed by Academician V.F. Utkin, was instructed to create a heavy rocket. In the same place, development work on a rocket with a lower launch mass was launched in parallel.

The heavy ICBM RS-20A went on its first test flight on February 21, 1973 from the Baikonur test site. Due to the complexity of the technical problems being solved, the development of the entire complex was delayed for two and a half years. At the end of 1975, on December 30, a new DBK with this missile was put on combat duty. Having inherited all the best from the R-36, the new ICBM has become the most powerful missile in its class.

The rocket is made according to the "tandem" scheme with a sequential separation of stages and structurally included the first, second and combat stages. Fuel tanks of the supporting structure were made of metal alloys. The separation of the stages was provided by the operation of explosive bolts.

ICBM RS-20A with monoblock warhead

The first-stage propulsion rocket engine combined four independent propulsion units into a single design. Control forces in flight were created by deflecting the nozzle blocks.

The propulsion system of the second stage consisted of a propulsion rocket engine, made according to a closed circuit and a four-chamber steering engine, made according to an open circuit. All liquid-propellant rocket engines were powered by high-boiling, self-igniting liquid fuel components on contact.

An autonomous inertial control system was installed on the rocket, the operation of which was provided by an onboard digital computer system. To increase the reliability of the BTsVK, all its main elements had redundancy. During combat duty, the onboard computer provided information exchange with ground devices. The most important parameters of the technical condition of the rocket were controlled by the control system. The use of BTsVK made it possible to achieve high firing accuracy. The QUO of the points of impact of warheads was 430 m.

ICBMs of this type carried particularly powerful combat equipment. There were two variants of warheads: monobloc, with a capacity of 24 Mt and MIRV with 8 individually targetable warheads with a capacity of 900 kt each. An improved complex for overcoming anti-missile defense systems was installed on the rocket.

ICBM RS-20B (USSR) 1980

The RS-20A missile, placed in a transport and launch container, was installed in an OS-type silo launcher in a refueled state and could be on combat duty for a long time. Preparation for the launch and launch of the rocket were carried out automatically after the control system received the launch command. To exclude unauthorized use of nuclear missile weapons, the control system accepted only commands specified by the code key. The implementation of such an algorithm was made possible by the introduction of a new system of centralized combat control at all command posts of the Strategic Missile Forces.

This missile was in service until the mid-80s, until it was replaced by the RS-20B. She, like all her contemporaries in the Strategic Missile Forces, owes her appearance to the development of neutron munitions by the Americans, new achievements in the field of electronics and mechanical engineering, and increasing requirements for the combat and operational characteristics of strategic missile systems.

The RS-20B ICBM differed from its predecessor by a more advanced control system and a combat stage refined to the level of modern requirements. Due to the powerful energy, the number of warheads on the MIRV was brought to 10.

The combat equipment itself has also changed. As the accuracy of shooting has increased, it has become possible to reduce the power of nuclear charges. As a result, the flight range of a rocket with a monoblock warhead was brought up to 16,000 km.

R-36 missiles have also been used for peaceful purposes. On their basis, a launch vehicle was created for launching spacecraft of the Kosmos series for various purposes into orbit.

Another brainchild of the Utkin Design Bureau was the PC-16A ICBM. Although she was the first to enter the tests (the launch at Baikonur took place on December 26, 1972), she was accepted into service on the same day along with the RS-20 and PC-18, the story of which is yet to come.

Rocket RS-16A - two-stage, with liquid fuel engines, made according to the "tandem" scheme with sequential separation of stages in flight. The rocket body has a cylindrical shape with a conical head. Fuel tanks of the supporting structure.

ICBM RS-20V in flight

Space rocket complex "Cyclone" based on the RS-20B

The propulsion system of the first stage consisted of a propulsion liquid-propellant rocket engine, made according to a closed circuit and a steering four-chamber liquid-propellant rocket engine, made according to an open circuit with rotary combustion chambers.

At the second stage, one sustainer single-chamber liquid-propellant rocket engine was installed, designed according to a closed circuit, with a part of the outflowing gas blown into the supercritical part of the nozzle to create control forces in flight. All rocket engines run on high-boiling, self-igniting on contact oxidizer and fuel. To ensure a stable operation of the engines, the fuel tanks were pressurized with nitrogen. Refueling of the rocket was carried out after installation in the launch shaft.

An autonomous inertial control system with an onboard computer system was installed on the rocket. It provided control of all missile systems during combat duty, pre-launch preparation and launch. The incorporated algorithms for the functioning of the control system in flight made it possible to ensure a firing accuracy (CVO) of no more than 470 m. The RS-16A missile was equipped with a multiple warhead with four individually targetable warheads, each of which contained a nuclear charge with a capacity of 750 kt.

ICBM PC-16A (USSR) 1975

1 - first stage, 2 - second stage, 3 - instrument compartment, 4 - tail compartment, 5 - head fairing, 6 - connecting compartment, 7 - first stage propulsion system, 8 - steering rocket engine, 9 - propulsion system mounting frame, 10 - first stage fuel tank, 11 - oxidant supply pipeline, 12 - first stage oxidizer tank, 13 - ASG line, 14 - second stage propulsion system attachment frame, 15 - second stage propulsion system, 16 - second stage fuel tank, 17 - second stage oxidizer tank, 18 - oxidizer tank pressurization line, 19 - CS electronic units, 20 - warhead, 21 - warhead fairing attachment hinge.

The great advantage of the new combat missile system was that the missiles were installed in silo launchers previously built for ballistic missiles of the first and second generations. It was necessary to carry out the necessary amount of work to improve some of the silo systems and it was possible to load new missiles. This resulted in significant financial savings.

On October 25, 1977, the first launch of the upgraded rocket took place, which received the designation RS-16B. Flight tests were carried out at Baikonur until September 15, 1979. On December 17, 1980, the DBK with a modernized missile was put into service.

The new missile differed from its predecessor by an improved control system (the accuracy of delivery of warheads increased to 350 m) and a combat stage. The multiple reentry vehicle installed on the rocket has also been upgraded. The combat capabilities of the missile have increased by 1.5 times, the reliability of many systems and the security of the entire DBK have increased. The first RS-16B missiles were put on combat duty in 1980, and at the time of signing the START-1 Treaty, 47 missiles of this type were in service with the Strategic Missile Forces.

ICBM RS-16A assembled without warhead (outside the launch canister)

The third missile that entered service during this period was the PC-18, developed at the Design Bureau of Academician V. Chelomey. This missile was supposed to harmoniously complement the strategic weapons system being created. Her first flight took place on April 9, 1973. Flight design tests took place at the Baikonur test site until the summer of 1975, after which the State Commission considered it possible to put the DBK into service.

Rocket PC-18 - two-stage, made according to the "tandem" scheme with sequential separation of stages in flight. Structurally, it consisted of the first, second stages, connecting compartments, an instrument compartment and an aggregate-instrument block with a split warhead.

The first and second stages constituted the so-called block of accelerators. All fuel tanks are load-bearing. The propulsion system of the first stage had four sustainer liquid-propellant rocket engines with rotary nozzles. One of the rocket engines was used to maintain the operating mode of the propulsion system in flight.

The propulsion system of the second stage consisted of a sustainer rocket engine and a steering liquid engine, which had four rotary nozzles. To ensure the stable operation of the rocket engines of the booster unit in flight, pressurization of the fuel tanks was provided.

All rocket engines operated on self-igniting stable propellant components. Refueling was carried out at the factory after the rocket was installed in the transport and launch container. However, the design of the pneumohydraulic system of the rocket and TPK made it possible, if necessary, to carry out operations for draining and subsequent refueling of rocket fuel components. The pressure in all rocket tanks was continuously monitored by a special system.

An autonomous inertial control system based on an onboard digital computer complex was installed on the rocket. When on combat duty, the SU, together with the ground-based TsVK, carried out control of the on-board systems of the missile and adjacent systems of the launcher. In all operational and combat modes, the rocket was carried out remotely from the command post of the DBK. The high performance of the control system was confirmed during test launches. The firing accuracy (KVO) was 350 m. The RS-18 carried an MIRV with six individually targetable warheads with a 550 kt nuclear charge and could hit enemy point targets that were highly protected and covered by missile defense systems.

The missile was “ampulized” in a transport and launch container, which was placed in silo launchers with a high degree of protection specially created for this missile complex.

The DBK with the PC-18 ICBM was a significant step forward even compared to the missile system with the RS-16A missile adopted at the same time. But as it turned out, in the process of operation, and he was not without flaws. In addition, during training and combat launches of missiles put on combat duty, a defect in the rocket engine of one of the stages was revealed. The matter took a serious turn. As always, there were also guilty “switchmen”. Colonel-General M.G. Grigoriev, First Deputy Commander-in-Chief of the Strategic Missile Forces, was removed from his post, whose only fault was that he was the chairman of the State Commission for testing the missile system with the RS-18 missile.

These failures hastened the adoption of the upgraded missile under the same RS-18 index with improved performance characteristics, flight tests of which have been carried out since October 26, 1977. In November 1979, the new DBK was officially adopted to replace its predecessor.

ICBM RS-18 (USSR) 1975

1 - body of the first stage; 2 - body of the second stage; 3 - sealed instrument compartment; 4 - combat stage; 5 - tail section of the first stage; 6 - head fairing; 7 - propulsion system of the first stage; 8 - fuel tank of the first stage; 9 - oxidizer supply pipeline; 10 - first stage oxidizer tank; 11 - cable box; 12 - main ASG; 13 - propulsion system of the second stage; 14 - power element of the body of the connecting compartment; 15 - fuel tank of the second stage; 16 - second stage oxidizer tank; 17- highway ASG; 18 - solid fuel brake engine; 19 - devices of the control system; 20 - combat unit.

On the improved rocket, the defects of the rocket engines of the booster unit were eliminated, while at the same time increasing their reliability, improving the characteristics of the control system, installing a new aggregate-instrument unit, which increased the flight range to 10,000 km, and increased the effectiveness of combat equipment.

The command post of the missile system has undergone significant modifications. A number of systems were replaced by more advanced and reliable ones. Increased the degree of protection against damaging factors of a nuclear explosion. The changes made have greatly simplified the operation of the entire combat missile system, which was immediately noted in the reviews from the military units.

From the second half of the 1970s, the Soviet Union began to experience a lack of financial resources for the harmonious development of the country's economy, which was caused not least by large expenditures on armaments. Under these conditions, the modernization of all three missile systems was carried out with the maximum degree of saving financial and material resources. Improved missiles were installed in place of the old ones, and in most cases modernization was carried out by bringing existing missiles to new standards.

The efforts made in the 1970s to further improve and develop missile weapons in our country played an important role in achieving strategic parity between the USSR and the USA. Adoption and deployment of third-generation missile systems equipped with individually guided MIRVs and means to overcome missile defense made it possible to achieve an approximate equality in the number of nuclear warheads on strategic launchers (excluding strategic bombers) of both states.

During these years, the development of ICBMs, like SLBMs, began to be influenced by a new factor - the process of limiting strategic arms. On May 26, 1972, during a summit meeting in Moscow, an Interim Agreement was signed between the Soviet Union and the United States of America on certain measures in the field of limiting strategic offensive arms, called SALT-1. It was concluded for a period of five years and entered into force on October 3, 1972.

The interim agreement established quantitative and qualitative restrictions on fixed ICBM launchers, SLBM launchers and ballistic missile submarines. The construction of additional land-based stationary ICBM launchers was prohibited, which fixed their quantitative level as of July 1, 1972 for each of the parties.

Modernization of strategic missiles and launchers was allowed on the condition that the launchers of light ground-based ICBMs, as well as ballistic missiles deployed before 1964, were not converted into launchers for heavy missiles.

In 1974-1976, in accordance with the Protocol on Procedures Governing the Replacement, Dismantling and Destruction of Strategic Offensive Arms, 210 launchers of R-16U and R-9A ICBMs with equipment and structures of launch positions were decommissioned and eliminated in the Strategic Missile Forces. The United States did not need to carry out such work.

On June 19, 1979, a new treaty between the USSR and the United States on the limitation of strategic arms was signed in Vienna, which was called the SALT-2 Treaty. If it came into force, each of the parties had to limit the level of strategic launchers to 2250 units from January 1, 1981. Subject to restrictions were carriers equipped with MIRVs for individual guidance. In the established total limit, they should not exceed 1320 units. Of this number, for PU ICBMs, the limit was set at 820 units. In addition, severe restrictions were imposed on the modernization of stationary launchers of strategic intercontinental missiles - it was forbidden to create mobile launchers of such missiles. It was allowed to conduct flight tests and deploy only one new type of light ICBM with a number of warheads not exceeding 10 pieces.

Despite the fact that the SALT-2 Treaty fairly and balancedly took into account the interests of both parties, the US administration refused to ratify it. And no wonder: the Americans thoughtfully approach their interests. By that time, most of their nuclear warheads were on SLBMs, and 336 missiles would have to be eliminated to fit into the established framework of restrictions on carriers. They were supposed to be either ground-based Minutemen-3 or naval Poseidons, recently adopted by modern SSBNs. At that time, tests of the new Ohio SSBN with the Trident-1 missile had just ended, and the interests of the American military-industrial complex could be seriously affected. In a word, from the financial side, this Treaty did not suit the government and the US military-industrial complex. However, there were other reasons to refuse to ratify it. But although the SALT-2 Treaty never entered into force, the parties still adhered to certain restrictions.

At that time, another state began to arm itself with intercontinental ballistic missiles. In the late 70s, the Chinese took up the creation of ICBMs. They needed such a missile to reinforce their claims to a leading role in the Asian region and the Pacific Ocean. With such weapons, it was possible to threaten the United States.

Flight design tests of the Dun-3 missile were carried out over a limited range - China did not have prepared test routes of considerable length. The first such launch was carried out from the Shuangengzi test site at a distance of 800 km. The second launch was carried out from the Uzhai test site at a range of about 2000 km. The tests were clearly delayed. Only in 1983, the Dong-3 ICBM (Chinese designation - Dongfeng-5) was adopted by the nuclear forces of the People's Liberation Army of China.

In terms of technical level, it corresponded to the Soviet and American ICBMs of the early 60s. A two-stage rocket with a sequential separation of stages had an all-metal body. The steps were joined together by means of a transition compartment of the truss structure. Due to the low energy characteristics of the engines, the designers had to increase the fuel supply in order to achieve the specified flight range. The maximum diameter of the rocket was 3.35 m, which is still a record figure for an ICBM.

The inertial control system, traditional for Chinese missiles, ensured a firing accuracy (KVO) of 3 km. "Dun-3" carried a monoblock nuclear warhead with a capacity of 2 Mt.

Remained low and the survivability of the complex as a whole. Despite the fact that the ICBM was placed in a silo launcher, its protection did not exceed 10 kg / cm? (by pressure in the front of the shock wave). For the 80s, this was clearly not enough. The Chinese missile lagged far behind the American and Soviet models of rocket technology in all the most important combat indicators.

ICBM "Dun-3" (China) 1983

Equipping combat units with this missile was slow. In addition, a launch vehicle was created on its basis to launch spacecraft into near-Earth orbits, which could not but affect the pace of production of military intercontinental missiles.

In the early 90s, the Chinese modernized the Dun-3. A significant jump in the level of the economy made it possible to raise the level of rocket science. Dun-ZM became the first Chinese MIRVed ICBM. It was equipped with 4-5 individually targeted warheads with a capacity of 350 kt each. Improved characteristics of the missile control system, which immediately affected the accuracy of fire (KVO was 1.5 km). But even after modernization, this missile, in comparison with foreign analogues, cannot be considered modern.

Let's go back to the US in the 1970s. In 1972, a special government commission was engaged in studying the prospects for the development of US strategic nuclear forces until the end of the 20th century. Based on the results of its work, President Nixon's administration issued an assignment to develop a promising ICBM capable of carrying MIRVs with 10 individually targetable warheads. The program received the MX code. The advanced research phase lasted six years. During this time, a dozen and a half projects of missiles with a launch weight of 27 to 143 tons, presented by various companies, were studied. As a result, the choice fell on the project of a three-stage rocket with a mass of about 90 tons, capable of being placed in the silo of Minuteman missiles.

In the period from 1976 to 1979, intensive experimental work was carried out both on the design of the rocket and on its possible basing. In June 1979, President Carter decided on the full-scale development of a new ICBM. The parent company was "Martin Marietta", which was entrusted with the coordination of all work.

In April 1982, bench fire tests of solid propellant rocket motors began, and a year later, on June 17, 1983, the rocket went on its first test flight at a range of 7600 km. He was considered quite successful. Simultaneously with flight tests, basing options were being developed. Initially, three options were considered: mine, mobile and air. So, for example, it was planned to create a special carrier aircraft, which was supposed to carry out combat duty by loitering in established areas and, on a signal, drop a missile, after having previously aimed it. After separation from the carrier, the main engine of the first stage was to be turned on. But this, as well as a number of other possible options, remained on paper. The US military really wanted to get the latest missile with a high degree of survivability. By that time, the main way was to create mobile missile systems, the location of the launchers of which could change in space, which created difficulties for delivering a targeted nuclear strike against them. But the principle of cost savings prevailed. Since the tempting aerial version was extremely expensive, and the Americans did not have time to fully work out the mobile ground (mobile underground) option, it was decided to place 50 new ICBMs in the modernized Minuteman-3 missile silos at the Warren missile base, and also continue testing mobile railway complex.

In 1986, the LGM-118A missile, called the Peekeper, entered service (in Russia it is better known as the MX). When it was created, the developers used all the latest in the field of materials science, electronics and instrumentation. Much attention was paid to reducing the mass of structures and individual elements of the rocket.

MX includes three march stages and a MIRV. All of them have the same design and consist of a body, a solid propellant charge, a nozzle block and a thrust vector control system. The solid propellant rocket engine of the first stage was created by Tiokol. Its body is wound from Kevlar-49 fibers, which have high strength and low weight. The front and rear bottoms are made of aluminum alloy. The nozzle block is deflectable with flexible supports.

The solid propellant rocket engine of the second stage was developed by Aerojet and differs structurally from the Tiokol engine in its nozzle block. The high-expansion deflectable nozzle has a telescopic type nozzle to increase the length. It is moved into the working position by means of a gas generating device after the separation of the rocket engine of the previous stage. To create control forces for rotation at the stage of operation of the first and second stages, a special system is installed, consisting of a gas generator and a control valve that redistributes the gas flow between two obliquely cut nozzles. The Hercules third-stage solid-propellant rocket engine differs from its predecessors in the absence of a thrust cut-off system, and its nozzle has two telescopic nozzles. Dual-mixture propellant charges are poured into ready-made rocket engine cases.

SPU ICBM RS-12M

The steps are interconnected by means of adapters made of aluminum. The entire body of the rocket from the outside is covered with a protective coating that protects it from heating by hot gases during launch and from the damaging factors of a nuclear explosion.

The inertial control system of the missile with the Meka-type BTsVK is located in the compartment of the MIRV propulsion system, which made it possible to achieve savings in the overall length of the ICBM. It provides flight control on the active part of the trajectory, at the stage of disengagement of warheads, and is also activated when the missile is on combat duty. The high quality of the GPS devices, accounting for errors and the use of new algorithms ensured a firing accuracy (CVO) of about 100 m. To create the required temperature regime, the control system in flight is cooled with freon from a special reservoir. The pitch and yaw angles are controlled by deflectable nozzles.

The MX ICBM is equipped with the Mk21 multiple reentry vehicle, consisting of a warhead compartment, closed by a fairing, and a propulsion unit compartment. The first compartment has a maximum capacity of 12 warheads, similar to the AP of the Minuteman-ZU missile. Currently, it houses 10 individually targeted warheads with a capacity of 600 kt each. Propulsion system with rocket engine of multiple inclusion. It is launched at the stage of operation of the third stage and ensures the breeding of all combat equipment. For the MIRV Mk21, a new set of means to overcome anti-missile defense systems has been developed, including light and heavy decoys, various jammers.

The rocket is placed in a container from which it is launched. For the first time, the Americans used a "mortar launch" to launch ICBMs from a silo launcher. The solid propellant gas generator, located in the lower part of the container, when triggered, ejects the rocket to a height of 30 m from the level of the mine protective device, after which the first-stage propulsion engine is turned on.

According to American experts, the combat effectiveness of the MX missile system is 6-8 times greater than the effectiveness of the Minuteman-3 system. In 1988, the deployment program for 50 Pikeper ICBMs ended. However, the search for ways to increase the survivability of these missiles has not ended. In 1989, a mobile railway missile system entered the test. It included a launcher car, a command and control car equipped with the necessary means of control and communication, as well as other cars that ensure the operation of the entire complex. At the training ground of the Ministry of Railways, this DBK was tested until mid-1991. Upon their completion, it was planned to deploy 25 trains with 2 launchers each. In peacetime, all of them were supposed to be at the point of permanent deployment. With the transfer to the highest degree of combat readiness, the command of the US strategic nuclear forces planned to disperse all the trains along the railway network of the United States of America. But the signing of the START Limitation and Reduction Treaty in July 1991 changed those plans. The railway missile system never entered service.

In the USSR, in the mid-1980s, the missile weapons of the Strategic Missile Forces were further developed. This was due to the implementation of the American strategic defense initiative, which provided for the launch of nuclear weapons and weapons based on new physical principles into space orbits, which created an exceptionally high danger and vulnerability for the strategic nuclear forces of the USSR throughout the territory. To maintain strategic parity, it was decided to create new silo and rail-based missile systems with RT-23 UTTKh missiles, similar in their characteristics to the American MX, and to modernize the RS-20 and PC-12 DBKs.

The first of them in 1985 received a mobile rocket launcher with the RS-12M missile. The accumulated wealth of experience in the operation of mobile ground systems (for operational-tactical missiles and medium-range missiles) allowed Soviet designers to create a practically new mobile complex on the basis of a mine-based intercontinental solid-propellant missile in a short time. The upgraded missile was placed on a self-propelled launcher, made on the chassis of a MAZ seven-axle tractor.

ICBM RS-12M in flight

In 1986, the State Commission adopted a railway missile system with RT-23UTTKh ICBMs, and two years later, the RT-23UTTKh, located in the silos previously used for RS-18 missiles, entered service with the Strategic Missile Forces. After the collapse of the USSR, 46 of the latest missiles ended up on the territory of Ukraine and are currently subject to liquidation.

All of these rockets are three-stage, with solid fuel engines. Their inertial control system ensures high firing accuracy. The RS-12M ICBM carries a single-block nuclear warhead with a capacity of 550 kt, and both modifications of the RS-22 carry an individually targetable MIRV with ten warheads.

The Rs-20V heavy intercontinental missile entered service in 1988. It is still the most powerful rocket in the world and is capable of carrying twice the payload of the American MX.

With the signing of the START-1 Treaty, the development of intercontinental missiles in the United States and the Soviet Union was suspended. At that time, each country was developing a complex with a small-sized missile to replace obsolete third-generation ICBMs.

The American program "Midgetman" was launched in April 1983 in accordance with the recommendations of the Scowcroft Commission, appointed by the US President to develop proposals for the development of land-based intercontinental missiles. Rather stringent requirements were set before the developers: to ensure a flight range of 11,000 km, reliable destruction of small targets with a monoblock nuclear warhead. In this case, the rocket was supposed to have a mass of about 15 tons and is suitable for placement in silos and on mobile ground installations. Initially, this program was given the status of the highest national priority, and work went on at full speed. Very quickly, two versions of a three-stage rocket with a launch weight of 13.6 and 15 tons were developed. After a competitive selection, it was decided to develop a rocket with a larger mass. Fiberglass and composite materials were widely used in its design. At the same time, a mobile protected launcher for this missile was being developed.

But with the intensification of work on SDI, there has been a tendency to slow down work on the Midgetman program. In early 1990, President Reagan gave instructions to curtail work on this complex, which was never brought to full readiness.

Unlike the American one, the Soviet DBK of this type was almost ready for deployment by the time the Treaty was signed. Flight tests of the rocket were in full swing and options for its combat use were developed.

Start of ICBM RS-22B

Currently, only China continues to develop ICBMs, seeking to create a missile that can compete with American and Russian designs. Work is underway on a solid rocket with MIRVs. It will have three sustainer stages with solid-fuel rocket engines and a launch weight of about 50 tons. The level of development of the electronics industry will allow (according to some estimates) to create an inertial control system capable of providing firing accuracy (CVO) of no more than 800 m. the new ICBM will be in silo launchers.

Strategic nuclear systems have long been turned into weapons of deterrence, and play more into the hands of politicians than the military. And, if strategic missiles are not completely eliminated, then both Russia and the United States will have to replace physically and morally obsolete ICBMs with new ones. What they will be, time will tell.

1. P-36M (SS-18 Satan), Russia (USSR) - 16,000 km

2. DongFeng 5А (DF-5A), China - 13,000 km.

3. R-29RMU2 Sineva (RSM-54, according to NATO classification SS-N-23 Skiff), Russia - 11,547 kilometers

4. UGM-133A Trident II (D5), USA - 11,300 kilometers

5. DongFeng 31 (DF-31A), China - 11,200 km

6. RT-2PM2 "Topol-M", Russia - 11,000 km

7. LGM-30G Minuteman III, USA - 10,000 km

8. M51, France - 10,000 km

9. UR-100N (SS-19 Stiletto), Russia - 10,000 km

10. RSM-56 Bulava, Russia - 10,000 km

R-36M "Satan"

RT-2PM2. "Topol M"

PC-24 "Yars"

SRK UR-100N UTTH with 15A35 rocket

15Ж60 "Well done"

R-30 "Mace"

X-101/X-102

R-36M "Satan"

RT-2PM2. "Topol M"

PC-24 "Yars"

SRK UR-100N UTTH with 15A35 rocket

15Ж60 "Well done"

R-30 "Mace"

X-101/X-102

Sections of this page:

ICBM R-7A (USSR) 1960

ICBM "Atlas-D" (USA) 1958

ICBM "Atlas-E" (USA) 1962

ICBM "Atlas-F" (USA) 1962

ICBM "Titan-1" (USA) 1961

Start of the ICBM "Titan-1"

ICBM R-16 (USSR) 1961

ICBM R-16 on parade

Installing the R-16 ICBM on the launch pad

ICBM "Minuteman-1B" and missile installer

ICBM R-9A (USSR) 1965

ICBM R-9A (USSR) 1965

ICBM "Titan-2" in flight

ICBM "Minuteman-2" in the silo

ICBM "Titan-2" (USA) 1963

ICBM PC-10 (USSR) 1971

ICBM UR-100 in TPK on parade

PC-10 ICBM assembly without warhead (outside the launch canister)

ICBM R-36 (USSR) 1967

ICBM R-36 on parade

ICBM R-36 at launch

RS-12, second and third stages without warhead

ICBM PC-12 (USSR) 1968

RS-12, first stage

ICBM "Minuteman-3" (USA) 1970

ICBM RS-20A with MIRV (USSR) 1975

ICBM RS-20A with monoblock warhead

ICBM RS-20B (USSR) 1980

ICBM RS-20V in flight

Space rocket complex "Cyclone" based on the RS-20B

ICBM PC-16A (USSR) 1975

ICBM RS-16A assembled without warhead (outside the launch canister)

ICBM RS-18 (USSR) 1975

ICBM "Dun-3" (China) 1983

SPU ICBM RS-12M

ICBM RS-12M in flight

Start of ICBM RS-22B

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