Orbital bombardment: the enemy is doomed to keep all-round defense. Russian ballistic missiles attack the US through the South Pole Orbital missiles

20.10.2019

Russia, in response to the US deployment of a third missile defense (ABM) position area in Eastern Europe can implement a program to create orbital ballistic missiles, RIA Novosti quotes the former chief of the Main Staff of the Rocket Forces strategic purpose(RVSN) of the Russian Federation, Vice-President of the Academy of Security, Defense and Law Enforcement, Colonel-General Viktor Yesin.

According to him, Russia may take technical and military measures in response to the US actions to deploy missile defense elements in Eastern Europe.

"For example, a program can be implemented to create orbital ballistic missiles capable of reaching US territory through the South Pole, bypassing US missile defense bases," Esin said.

According to him, from such missiles at one time Soviet Union refused under the START-1 Treaty. Such technical measures can be implemented already now. As for military measures, now it is clearly premature, since "the third positional area is still virtual, and Russia should not scare Europe yet," the expert added.

According to Esin, technical measures could also include equipping new Russian ballistic missiles with maneuverable warheads. Among the possible military measures, the ex-commander-in-chief of the Strategic Missile Forces named the deployment in Kaliningrad of the Iskander system with ballistic and cruise missiles, basing Tu-22M3 long-range bombers equipped with high-precision weapons at forward airfields, as well as the suspension of Russia's participation in the Russian-American Strategic Offensive Reductions Treaty.

"In any case, there can be no doubt that the Russian military will take into account the deployment of US missile defense elements in Europe in nuclear and military planning," the general said.

In turn, the chief researcher of the Center international security Institute of World Economy and international relations, Major General Vladimir Dvorkin expressed the opinion that there is no big threat to the Russian nuclear missile defense potential of the United States in Eastern Europe, Interfax reports.

"For the Russian nuclear deterrence potential, this system poses absolutely no danger," the expert said. Dvorkin explained that in order to shoot down one Russian warhead, about 10 anti-missiles would be needed, that is, almost everything that is planned to be deployed in Poland. "And we can have many hundreds of such warheads," the general stressed.

Sergey Lavrov: we need to speed up the process of negotiations on START-1 and agree on missile defense

Recall that on the eve of Russia called on the United States to clarify the situation on missile defense, since Moscow has not yet received specific and clear proposals in this area.

According to Russian Foreign Minister Sergei Lavrov after a meeting with US Secretary of State Condoleezza Rice as part of the ongoing ASEAN events in Singapore.

"We discussed in detail almost all issues on our bilateral agenda and the prospects for cooperation on international and regional affairs," he said. Special attention on our part, the need was nevertheless given to clarify the situation on missile defense, where the transparency and confidence-building measures promised to us by our American colleagues have not yet materialized into something concrete and tangible. "Lavrov calls on the United States to work out concrete steps to strengthen measures confidence in the missile defense sphere, ITAR-TASS reports.

“We also drew attention to the need to speed up the process of negotiations on strategic offensive arms limitations, in preparation for the fact that the START-1 treaty will expire at the end of 2009,” Lavrov continued, “and we do not want to leave a vacuum in this critical area regarding strategic stability".

The USSR began developing an orbital ballistic missile back in the 1960s. But in 1983 she was removed from combat duty under OSV-2

Development of a strategic missile system R-36 with an 8K69 orbital missile based on the 8K67 intercontinental ballistic missile was assigned by the Decree of the Central Committee of the CPSU and the Council of Ministers of the USSR of April 16, 1962. The creation of the rocket and the orbital unit was entrusted to OKB-586 (now KB Yuzhnoye; Chief Designer M.K. Yangel), rocket engines - OKB-456 (now NPO Energomash; Chief Designer V.P. Glushko), control system - NII-692 (now Design Bureau "Khartron"; Chief Designer V.G. Sergeev), command instruments - NII-944 (now NIIKP; Chief Designer V.I. Kuznetsov). The combat launch complex was developed at KBSM under the leadership of Chief Designer E.G. Rudyak.

Orbital missiles provide the following advantages over ballistic missiles:

Unlimited flight range, which allows hitting targets inaccessible to ballistic intercontinental missiles;

The possibility of hitting the same target from two mutually opposite directions, which forces a potential enemy to create missile defense from at least two directions and spend much more money. For example, the defensive line from the northern direction - "Safeguard", cost the US tens of billions of dollars.;

Less flight time of the orbital warhead in comparison with the flight time of the warhead of ballistic missiles (when launching an orbital missile in the shortest direction);

The impossibility of predicting the area of impact of the warhead of the warhead when moving in the orbital section;

The ability to provide satisfactory accuracy of hitting the target at very long launch ranges;

The ability to effectively overcome the existing anti-missile defense of the enemy.

Already in December 1962, a preliminary design was completed, and in 1963, the development of technical documentation and the manufacture of prototypes of the rocket began. Flight tests were completed on May 20, 1968. Adopted by the Decree of the Government of the USSR of November 19, 1968.

The first and only regiment with 8K69 orbital missiles took up combat duty on August 25, 1969. at NIIP-5. The regiment deployed 18 launchers.

Orbital rockets 8K69 were removed from combat duty in January 1983. in connection with the conclusion of the Treaty on the Limitation of Strategic Arms (SALT-2), which stipulated a ban on such systems. Later, on the basis of the 8K69 rocket, the Cyclone family of launch vehicles was created.

NATO code - SS-9 Mod 3 "Scarp"; in the USA it also had the designation F-1-r.

The use of space technology for military purposes has always been of paramount importance in the Soviet Union. Some programs were entirely military-oriented, others provided for their dual use, and others simply pretended to be possible military use. There was nothing surprising in this state of affairs, since in the vast majority of cases the Ministry of Defense acted as a customer, and, quite naturally, ordered the music.

One program that was developed exclusively for military use was the "partial orbital bombardment" system, or better known by its English abbreviation "FOBS". Its creation can be viewed as a logical continuation of the work begun at the time in the design bureau of Sergei Pavlovich KOROLEV and envisaged the development of a global missile "GR-1" capable of hitting targets on enemy territory from any direction. Although the royal rocket was created, it was not accepted into service. One of the reasons for this decision was the development in the design bureau of Mikhail Kuzmich YANGEL of a more powerful R-36orb missile, capable of more effectively solving the problem of delivering a nuclear warhead to the target.

The development of "R-36orb" (product index - 8K69; in various sources there are other rocket designations: OR-36 or R-36-0; NATO code - SS-9 Mod 3 "Scarp"; in the USA it also had the designation F- 1-r) based on the intercontinental ballistic missile "R-36" was set by the Decree of the Central Committee of the CPSU and the Council of Ministers of the USSR of April 16, 1962. The creation of the rocket and the orbital block for it was entrusted to OKB-586 (now Yuzhnoye Design Bureau; Chief Designer Mikhail Kuzmich YANGEL), rocket engines - OKB-456 (now NPO Energomash; Chief Designer Valentin Petrovich GLUSHKO), control system - Research Institute -692 (now Khartron Design Bureau; Chief Designer Vladimir Grigorievich SERGEEV), command instruments - NII-944 (now NII KP; Chief Designer Viktor Ivanovich KUZNETSOV). The combat launch complex for R-36orb missiles was developed at KBSM under the leadership of Chief Designer Evgeny Georgievich RUDIAK.

Already in December 1962, a preliminary design was completed, and in 1963, the development of technical documentation and the manufacture of prototypes of the rocket began.

The created rocket had two stages. Its total length was 32.6 - 34.5 m, the maximum body diameter was 3.05 m. At the start, the rocket weighed 180 tons. The firing range was 40,000 km, and the circular probabilistic deviation was -1,100 m. km. How the actual parameters of the orbits of the orbital blocks corresponded to the calculated ones can be seen in Table 1, which shows the main data on the launches that took place. The control system was supposed to be inertial with a gyro-stabilized platform, the aiming system was based on ground-based instruments. The separation of the stages and the separation of the orbital block was supposed to take place using braking rocket solid propellant engines (RDTT). The rocket was to be launched from a silo launcher. Start type - gas dynamic. The launch preparation time is only 5 minutes, which favorably distinguished the R-36orb from the first rocket of this class, the GR-1, where the preparation time was much longer.

The first stage had a length of 18.9 m and a diameter of 3 m. Its dry weight was 6.4 tons, and when loaded, the stage weighed 122.3 tons. 2 cameras each), developed in OKB-456. The engine provided thrust in the void of 270.4 tf and an operating time of 120 s. The steering engine RD-68M, developed in OKB-586, could work for 125 s and provide 295 kN thrust in the void.

The second stage had a length of 9.4 m and a diameter of 3 m. Its dry weight was 3.7 tons, and together with fuel 49.3 tons. 120 tf and operating time 160 s. The RD-69M steering engine with four steering chambers had a thrust of 54.3 kN and an operating time of 163 s.

As a fuel, the engines of both stages used asymmetric dimethylhydrazine (UDMH), whose weight was 48.5 tons, and nitrogen tetroxide (AT) weighing 121.7 tons as an oxidizer.

The 8F021 orbital combat unit, which distinguished the R-36orb missile from the R-36 ICBM, consisted of a body, an instrument compartment with a control system, a thermonuclear monoblock charge weighing 1700 kg and a power of 5 Mt, as well as a brake propulsion system (TDU ), which brought the unit out of low Earth orbit and ensured the delivery of the charge to the target. The separation of the TDU from the warhead occurred by relieving pressure from the fuel tanks through special nozzles.

Flight design tests of the R-36orb missile were planned according to the standard scheme in four interconnected stages. The first stage provided for the development of the launch vehicle itself, the second - the development of the launch of the orbital unit into near-Earth orbit, the third - the development of the "partial-orbital bombing" system as a whole, the fourth, test, - the delivery of the system to the customer with the elimination of the comments identified in the previous stages.

The first stage began on December 16, 1965 with a launch from a ground-based launcher located at site No. 67 of the Tyura-Tam test site (for simplicity of narration and in order to avoid confusion, I will call the Tyura-Tam test site by a more familiar name - the Baikonur Cosmodrome), rockets "R- 36orb". Instead of the orbital block, its weight and size mock-up was installed on the carrier. The launch into low Earth orbit was not planned, and the launch was carried out solely to test the onboard systems of the carrier and ground equipment. In general, despite some minor shortcomings, everything went well.

The following year, the first stage of the LCI was continued. On February 5, March 16 and May 19, 1966, three more launches were carried out, and during the third, the rocket was launched for the first time from a silo launcher at site No. 69. and the tests themselves were carried out in order to refine the systems and assemblies of the carrier. The launches were considered successful.

Since, unfortunately, there is no way to get acquainted with the technical documentation about these launches, one has to rely only on the available publications about them, based either on the recollections of eyewitnesses or on Western intelligence data, which are cited in numerous foreign sources. These data do not allow us to state unequivocally that in 1966 only three test flights of the R-36orb rocket were carried out as part of the first stage of testing. Some sources report that in 1966, four launches were carried out as part of the LCI. The resulting inaccuracy can have two possible explanations. Or, speaking of four launches, the sources also take into account the launch on December 16, 1965, erroneously summing it up with the launches of the next year. Either there really were four launches, but the author does not have any information about the fourth.

The second stage of the LCI was launched in the autumn of 1966 and included two launches of the R-36orb rocket. Since both launches are of interest from the point of view of the history of astronautics, I will dwell on them in more detail.

On September 17, 1966, the R-36orb rocket was launched from the silo launcher at the 69th site of the Baikonur Cosmodrome (not to repeat every time, all subsequent launches came from the silo launchers at this site of the cosmodrome). Nine minutes later, the head unit of the rocket entered low-Earth orbit. Officially, the launch, like any other launch of a combat missile (with rare exceptions), was not reported. However, Western surveillance equipment recorded the appearance in low Earth orbit, first of one object, which was registered in the US Space Command catalog under the number 02437 (in the COSPAR registry, the launch was designated 1966-088), and after some time 52 more small objects identified as having arisen in the result of this launch. In Soviet publications for a long time this launch appeared for a long time under the name - "No data". I remember that the Aviation and Cosmonautics magazine at the end of the 60s tried to attribute all such launches (8 such launches were mentioned in Soviet publications) to either France or China. The truth surfaced in the late 80s. In Table 2, for reference, I provide data on these launches, although only two are related to the program for creating a "partial-orbital bombardment" system.

But back to the tests on September 17, 1966. There is still no clarity regarding the results of this test launch. We only know that the object exploded in orbit. But whether this was done intentionally or the explosion occurred arbitrarily is unknown. In favor of success is the fact that this launch was the first launch of the R-36 rocket with the launch of the warhead into low Earth orbit. On the other hand, the fact of an explosion in orbit, the absence of an official announcement, as well as orbital elements different from further launches, may testify in favor of negative result. It is most logical to assume that, when trying to deorbit the orbital unit, the TDU did not work and the emergency destruction system, which was installed on almost all Soviet spacecraft in those years, was put into action. However, it is also quite logical that by the time of this launch, the TDU was simply not yet ready, and at this stage only the orbital unit itself, which was not equipped with a TDU, was tested. For a long time it seemed to me that the version of the emergency launch was correct, but after much deliberation, I began to lean towards the version of the absence of a TDU on the orbital block. Based on this, I attribute the two launches of 1966 to the second stage of the LKI, and do not combine them with either earlier or later launches of R-36orb missiles.

A similar launch, which was also not officially announced, but COSPAR assigned its number 1966-101 to it, took place on November 2, 1966. Its only difference from the previous one was the number of debris in orbit. This time there were slightly fewer of them - 40.

Further launches as part of the creation of a partially orbital bombing system were officially reported as the next launches of satellites of the Kosmos series, naturally without deciphering their true purpose.

In 1967, the third stage of the LCI was quite intense. 9 launches were carried out with the launch of the orbital unit into low Earth orbit. According to other data, there were 10 launches. The situation with the R-36orb launch on March 22, 1967 is not entirely clear. It was not officially reported about it, the US Space Command did not record the appearance of objects in orbit, but did not report an emergency rocket launch either. Again, you have to guess and express your versions. It is likely that the flight program was not fully implemented. The orbital stage, for one reason or another, did not enter orbit, but flew along a suborbital trajectory. This explains why American surveillance equipment could not detect any objects in orbit. But, on the other hand, since all space objects that arose during the implementation of this program were short-lived, it is quite possible that the Americans simply “slept through” the launch, and in the Soviet Union they “forgot” to announce the launch of the next Cosmos (by the way, all reports of the launch of the next satellites during the implementation of the test program of the "partial-orbital bombardment" system appeared only after they were registered by the US Space Command). That is, they acted on the principle that once they saw it, it meant it happened, but if they didn’t see it, it means it didn’t happen. In general, the launches were successful, but the targeting system caused criticism, which did not allow achieving the required accuracy, as well as a number of other comments made by the military.

The American side first reported that the Soviet Union was testing a "partial orbital bombardment" system only on November 3, 1967. By that time, the main tests had already been completed, and the developers eliminated the comments made by the customer during the test launches.

In 1968, two (according to other sources, four) launches of No. R-36orb missiles were carried out. "If the picture is quite clear with respect to launches on April 25 and October 2, then launches on May 21 and 28 do not give a clear picture. During May launches, no the appearance of any objects in near-Earth orbit.Most likely, they were classified as R-36orb launches erroneously, since at the same time flight design tests of the R-36 ICBM, which, in terms of its tactical and technical parameters, was very close to the R -36orb". However, I admit that these could also be R-36orb launches, but at the same time it was possible to hide the fact that the orbital stage entered the near-Earth orbit (after all, it is not so omnipotent technical intelligence United States, as they are now trying to present). It is quite possible that during these launches only the carrier itself and its reliability were tested, but not the "partial-orbital bombardment" system as a whole.

Be that as it may, on November 19, 1968, the system of "partial-orbital bombardment" as part of the R-36orb launch vehicle and the 8F021 orbital unit was put into service. The first missile regiment with R-36orb ICBMs took up combat duty on August 25, 1969 at the Baikonur cosmodrome (the regiment commander was A.V. Mileev).

The regiment included 18 mine launchers, combined into three combat launch complexes (6 silos in each BSK). Each shaft had a shaft diameter of 8.3 m and a height of 41.5 m. The distance between the mine launchers was 6–10 km.

The regiment was the only one in the Strategic Missile Forces armed with these missiles.

In subsequent years, launches were carried out with a frequency of one or two times a year and their task was to maintain the combat readiness of the system. In 1971, the last launch on a partial orbital trajectory was carried out. No further launches were made. Several reasons can serve as an explanation for this. First, the system was not as efficient as we would like. Secondly, it was quite vulnerable due to the silo-based missiles. Thirdly, the United States created and put into operation a fairly effective early detection and warning system, which was able to detect a missile at the moment of its launch, and not on the approach trajectory. Fourth, international détente and Soviet-American talks on strategic arms reduction began.

In the United States, a system similar to the partial orbital bombing system was not created, although in the early 60s the US military seriously studied this issue. The idea was not supported due to the high cost of deploying a full-scale system.

And a few words at the end.

On July 18, 1979, in Vienna (Austria), the General Secretary of the CPSU Central Committee, Chairman of the Presidium of the Supreme Soviet of the USSR Leonid Ilyich BREZHNEV and US President Jimmy CARTER signed the "Treaty between the Union of Soviet Socialist Republics and the United States of America on the Limitation of Strategic Offensive Arms" (SALT-2 Treaty ).

One of the provisions of the Treaty forbade the parties to have weapons systems like FOBS. Of the 18 mine launchers deployed by that time, 12 were to be eliminated, and the remaining 6 were to be converted for testing modernized intercontinental ballistic missiles.

By January 1983, work on the elimination of R-36orb missiles was completed, and the system was withdrawn from service.

If we evaluate the partial-orbital bombing system from today's positions, then we cannot speak about its effectiveness as a weapon system. Its creation and deployment was due primarily to political reasons. This is supported by the deployment of a small number of R-36orb missiles, as opposed to the mass deployment of R-36 missiles. The liquidation of the system as a type of weapon was also due to political reasons. It is of the greatest interest from a historical point of view.

To date Russian Federation has the most powerful space industry in the world. Russia is the undisputed leader in the field of manned cosmonautics and, moreover, has parity with the United States in matters of space navigation. Some lags in our country are only in the research of distant interplanetary spaces, as well as in developments in remote sensing of the Earth.

Story

The space rocket was first conceived by Russian scientists Tsiolkovsky and Meshchersky. In 1897-1903 they created the theory of its flight. Much later, foreign scientists began to master this direction. These were the Germans von Braun and Oberth, as well as the American Goddard. In peacetime between the wars, only three countries in the world dealt with issues of jet propulsion, as well as the creation of solid-fuel and liquid engines for this purpose. These were Russia, the USA and Germany.

Already by the 40s of the 20th century, our country could be proud of the successes achieved in the creation of solid fuel engines. This made it possible to use such formidable weapons as Katyushas during World War II. As for the creation of large rockets equipped with liquid engines, Germany was the leader here. It was in this country that the V-2 was adopted. These are the first short-range ballistic missiles. During World War II, the V-2 was used to bomb England.

After the victory of the USSR over Nazi Germany, the main team of Wernher von Braun, under his direct leadership, launched its activities in the United States. At the same time, they took with them from the defeated country all the previously developed drawings and calculations, on the basis of which the space rocket was to be built. Only a tiny part of the team of German engineers and scientists continued their work in the USSR until the mid-1950s. At their disposal were separate parts of technological equipment and missiles without any calculations and drawings.

Later, both in the USA and in the USSR, V-2 rockets were reproduced (in our case it is R-1), which predetermined the development of rocket science aimed at increasing the flight range.

Tsiolkovsky's theory

This great Russian self-taught scientist and outstanding inventor is considered the father of astronautics. Back in 1883, he wrote the historical manuscript "Free Space". In this work, Tsiolkovsky for the first time expressed the idea that movement between planets is possible, and a special one is needed for this, which is called a "space rocket". The very theory of the reactive device was substantiated by him in 1903. It was contained in a work called "Investigation of the World Space". Here the author cited evidence that a space rocket is the apparatus with which you can leave the limits earth's atmosphere. This theory was a real revolution in the scientific field. After all, mankind has long dreamed of flying to Mars, the Moon and other planets. However, pundits have not been able to determine how an aircraft should be arranged, which will move in an absolutely empty space without a support capable of giving it acceleration. This problem was solved by Tsiolkovsky, who proposed the use for this purpose. Only with the help of such a mechanism it was possible to conquer space.

Operating principle

Space rockets of Russia, the USA and other countries are still entering the Earth's orbit with the help of rocket engines, proposed at the time by Tsiolkovsky. In these systems, the chemical energy of the fuel is converted into kinetic energy, which is possessed by the jet ejected from the nozzle. A special process takes place in the combustion chambers of such engines. As a result of the reaction of the oxidizer and fuel, heat is released in them. In this case, the combustion products expand, heat up, accelerate in the nozzle and are ejected at great speed. In this case, the rocket moves due to the law of conservation of momentum. She receives acceleration, which is directed in the opposite direction.

To date, there are such engine projects as space elevators, etc. However, in practice they are not used, as they are still in development.

First spacecraft

The Tsiolkovsky rocket, proposed by the scientist, was an oblong metal chamber. Outwardly, it looked like a balloon or airship. The front, head space of the rocket was intended for passengers. Control devices were also installed here, as well as carbon dioxide absorbers and oxygen reserves were stored. Lighting was provided in the passenger compartment. In the second, main part of the rocket, Tsiolkovsky placed combustible substances. When they were mixed, an explosive mass was formed. She was ignited in the place allotted to her in the very center of the rocket and was thrown out of the expanding pipe at great speed in the form of hot gases.

For a long time the name of Tsiolkovsky was little known not only abroad, but also in Russia. Many considered him a dreamer-idealist and an eccentric dreamer. The works of this great scientist received a true assessment only with the advent of Soviet power.

Creation of a missile complex in the USSR

Significant steps in the exploration of interplanetary space were made after the end of World War II. It was a time when the United States, being the only nuclear power, began to exert political pressure on our country. The initial task that was set before our scientists was to increase military power Russia. For a worthy rebuff in the conditions unleashed in these years cold war it was necessary to create an atomic, and then the second, no less difficult task, was to deliver the created weapons to the target. For this they required combat missiles. In order to create this technique, already in 1946 the government appointed chief designers of gyroscopic instruments, jet engines, control systems, etc. S.P. became responsible for linking all systems into a single whole. Korolev.

Already in 1948, the first of the ballistic missiles developed in the USSR was successfully tested. Similar flights in the USA were carried out a few years later.

Launch of an artificial satellite

In addition to building up military potential, the government of the USSR set itself the task of developing outer space. Work in this direction was carried out by many scientists and designers. Even before an intercontinental-range missile took off into the air, it became clear to the developers of such technology that by reducing the payload of an aircraft, it was possible to achieve speeds exceeding space speed. This fact spoke about the probability of launching an artificial satellite into the earth's orbit. This landmark event took place on October 4, 1957. It became the beginning of a new milestone in the exploration of outer space.

The work on the development of airless near-Earth space required enormous efforts on the part of numerous teams of designers, scientists and workers. The creators of space rockets had to develop a program for launching an aircraft into orbit, debug the work of the ground service, etc.

The designers faced a difficult task. It was necessary to increase the mass of the rocket and make it possible for it to reach the second. That is why in 1958-1959 a three-stage version of a jet engine was developed in our country. With his invention, it became possible to produce the first space rockets in which a person could rise into orbit. Three-stage engines also opened up the possibility of flying to the moon.

Further, boosters have been more and more improved. So, in 1961, a four-stage model of a jet engine was created. With it, the rocket could reach not only the Moon, but also get to Mars or Venus.

First manned flight

The launch of a space rocket with a man on board took place for the first time on April 12, 1961. The Vostok spacecraft piloted by Yuri Gagarin took off from the Earth's surface. This event was epochal for mankind. In April 1961 space exploration received its new development. The transition to manned flights required designers to create such aircraft, which could return to Earth, safely overcoming the layers of the atmosphere. In addition, a human life support system was to be provided on the space rocket, including air regeneration, food, and much more. All these tasks were successfully solved.

Further space exploration

Vostok-type missiles for a long time helped to maintain the leading role of the USSR in the field of research into near-Earth airless space. Their use continues to the present day. Until 1964, Vostok aircraft surpassed all existing analogues in terms of their carrying capacity.

Somewhat later, more powerful carriers were created in our country and in the USA. The name of space rockets of this type, designed in our country, is Proton-M. American similar device - "Delta-IV". In Europe, the Ariane-5 launch vehicle, belonging to the heavy type, was designed. All these aircraft make it possible to launch 21-25 tons of cargo to a height of 200 km, where low earth orbit is located.

New developments

As part of the project of manned flight to the moon, launch vehicles belonging to the superheavy class were created. These are such US space rockets as the Saturn-5, as well as the Soviet H-1. Later, the super-heavy Energia rocket was created in the USSR, which is currently not used. The Space Shuttle became a powerful American launch vehicle. This rocket made it possible to launch spacecraft weighing 100 tons into orbit.

Aircraft manufacturers

Space rockets were designed and built at OKB-1 (Special Design Bureau), TsKBEM (Central Design Bureau of Experimental Engineering), as well as at NPO (Scientific and Production Association) Energia. It was here that domestic ballistic missiles of all types saw the light. Eleven strategic complexes came out of here, which our army adopted. Through the efforts of the employees of these enterprises, the R-7 was also created - the first space rocket, which is considered the most reliable in the world at the present time. Since the middle of the last century, these production facilities initiated and carried out work in all areas related to. Since 1994, the enterprise received a new name, becoming RSC Energia OJSC.

Space rocket manufacturer today

RSC Energia im. S.P. The Queen is a strategic enterprise of Russia. It plays a leading role in the development and production of manned space systems. great attention at the enterprise is given to the creation of the latest technologies. Specialized automatic space systems are being developed here, as well as launch vehicles for launching aircraft into orbit. In addition, RSC Energia is actively implementing high-tech technologies for the production of products that are not related to the development of airless space.

As part of this enterprise, in addition to the head design bureau, there are:

CJSC "Plant of experimental engineering".

CJSC PO Cosmos.

CJSC "Volzhskoye KB".

Branch "Baikonur".

The most promising programs of the enterprise are:

Issues of further space exploration and the creation of a manned transport space system of the latest generation;

Development of manned aircraft capable of mastering interplanetary space;

Design and creation of energy and telecommunication space systems using special small-sized reflectors and antennas.

In 1962, the USSR began the development of three projects of so-called global or orbital rockets - R-36-0 in OKB-586 of Mikhail Yangel, GR-1 in OKB-1 of Sergey Korolev and UR-200A in OKB-52 of Vladimir Chelomey. Only the R-36-0 was adopted for service (the press also gives a variant of the name R-36 orb).

The development of the rocket in OKB-586 under the leadership of Mikhail Yangel began on April 16, 1962 after the government decree "On the creation of samples of intercontinental ballistic and global missiles and carriers of heavy space objects" was issued. "Orbital missiles provide the following advantages over ballistic missiles:

unlimited flight range, which allows hitting targets inaccessible to ballistic intercontinental missiles;

the possibility of hitting the same target from two mutually opposite directions;

shorter flight time of the orbital warhead compared to the flight time of the warhead of ballistic missiles (when launching an orbital rocket in the shortest direction);

the impossibility of predicting the area where the warhead of the warhead will fall when moving in the orbital sector;

the possibility of ensuring satisfactory accuracy of hitting the target at very long launch ranges.

The main advantage of the R-36 Orb orbital rocket. was its ability to effectively overcome the enemy's anti-missile defense ". (Intercontinental ballistic missiles of the USSR (RF) and the USA. History of creation, development and reduction / Edited by E.B. Volkov. - M .: RVSN, 1996. P. 135 ).

The energy capabilities of the R-36 rocket made it possible to launch a nuclear warhead into space into low orbit. The mass of the warhead and the power of the warhead were reduced, but the most important quality was achieved - invulnerability to missile defense systems. The missile could strike at US territory not from the northern direction, where a missile defense system with missile attack warning stations was being built, but from south direction where the United States did not have a missile defense system.

The preliminary design of a two-stage orbital rocket was developed in December 1962.

"In the orbital version (rocket 8K69), in addition to the warhead, the orbital warhead (ORB) of the rocket includes a control compartment. Here the propulsion system and control devices for orientation and stabilization of the warhead (MC) are located. The brake engine of the OGCh is single-chamber. Its turbopump unit (TNA) is started from a powder starter.The engine runs on the same propellant components as the rocket engines... Stabilization of the HF in pitch and yaw in the active deceleration section during descent from orbit is performed by four fixed nozzles operating on the exhaust gases of the turbine. in the nozzles is regulated by throttle devices.Roll stabilization is carried out by four tangentially located nozzles.The system of orientation, control and stabilization (CSOS) of the OGCh is autonomous, inertial.It is supplemented by a radio altimeter that controls the orbital height twice - at the beginning of the orbital segment and before applying the braking impulse.

The brake motor is mounted in the central part of the control compartment inside the toroidal fuel module. The adopted form of fuel tanks made it possible to make the layout of the compartment optimal and reduce the weight of its structure. Dividing nets and baffles are installed inside the fuel tanks to ensure the reliability of starting and operating the engine in a state of weightlessness, ensuring reliable cavitation-free operation of the engine pumps. The brake propulsion system creates an impulse, transferring the HCV from an orbital trajectory to a ballistic one. On combat duty, the HRC is stored, like a rocket, in a refueled state. 1997, p. 180).

The first stage of the rocket is equipped with an RD-261 main engine, consisting of three two-chamber RD-260 modules. The second stage is equipped with a two-chamber main engine RD-262. The engines were developed at Energomash Design Bureau under the direction of Valentin Glushko. The fuel components are UDMH and nitrogen tetroxide (AT).

The launch equipment units of the ground complex for testing the rocket at the Baikonur test site were developed at KBTM.

"With the creation of the complex (launch complex - ed.) 8P867, work at site No. 67 of Baikonur was not completed. When the next rocket 8K69 of the Yangel Design Bureau arrived, the second launch pad of this complex was reconstructed to ensure its flight testing. The new launch complex received the index 8P869 The similarity of the parameters and technology for the preparation of 8K69 and 8K67 rockets required the creation of a relatively small number of new launch units, seven of which were developed by GSKB (KBTM - ed.) and seven by related enterprises. Basically, ground equipment was modified and unified for both missiles The new complex was tested, was put into operation and in the period 1965-1966 ensured the preparation and launch of 4 8K69 missiles. " (Kozhukhov N.S., Solovyov V.N. Complexes of ground-based equipment for rocket technology. 1948-1998 / Edited by Doctor of Technical Sciences Prof. Biryukov G.P. - Moscow, 1998. P 55). Initially, the ampulization of the R-36-0, like the R-36 missiles, was not provided for. Ampullization work began after the GKOT order of January 12, 1965 was issued.

R-36-O on launcher

At the end of 1964, preparations for testing began at Baikonur. The first launch of the R-36-O was made on December 16, 1965. Testing completed in May 1968.

Recalls retired colonel Georgy Smyslovskikh:

"Testing of the R-36-O missile began at the end of 1965. The Deputy Head of the F.E. Dzerzhinsky Military Academy, Lieutenant-General Fedor Petrovich Tonkikh, was appointed Chairman of the State Commission for Missile Testing. The first launch of the R-36-0 missile on December 16, 1965 of the year was emergency. During the completion of refueling of the 2nd stage with fuel, in the receiver, from which the fuel tanks were pressurized with nitrogen, a nitrogen leak began. Considering that the nitrogen supply was for two refuelings, we could tests sent management specialists to the receiver, during the work of which, to search for nitrogen etching, a false command was received to shoot the fillers of the 2nd stage. The fillers undocked, fuel poured from a height onto the concrete, ignited from the impact, and a fire started.(The creators of nuclear missile weapons and veterans-rocketmen tell. - M .: TSIPK, 1996. P. 210). In 1966, four successful test launches were carried out.

"It should be noted that in December 1965 (the date needs to be clarified - author's note) the global rocket 8K69 was launched. warhead, which, having made one revolution around the Earth, fell into a given area with deviations from the calculated point of impact in range and direction, corresponding to those specified by the tactical and technical requirements of the Ministry of Defense (TTT MO).(Baikonur. Korolev. Yangel / Compiled by M. I. Kuznetsky. - Voronezh: IPF "Voronezh", 1997. P. 181).

By a government decree on November 19, 1968, the R-36-0 orbital rocket was put into service. The complexes in the silo OS were put on combat duty at the Baikonur training ground on August 25, 1969. Serial production is deployed at the Southern Machine-Building Plant in Dnepropetrovsk.

18 launchers of R-36-0 orbital missiles with nuclear warheads were deployed by 1972 in a single positional area - at the Baikonur test site.

The missile brigade for the operation of the R-36-0 was formed in October 1969. By July 1979, on the basis of the brigade administration, as well as the administrations of individual engineering test units that launched the R-36 and R-16 missiles, the administration of individual engineering test units (OIICh) was formed at Baikonur.

In 1982, the Baikonur test site was transferred to the Main Directorate of Space Facilities of the Ministry of Defense (GU-KOS). In January 1983, in accordance with the SALT-2 treaty, the R-36-0 missile system was removed from combat duty. By November 1, 1983, the management of the OIICh at Baikonur was disbanded.

Development R-36 strategic missile system with 8K69 orbital missile based on the intercontinental ballistic missile 8K67 was set by the Decree of the Central Committee of the CPSU and the Council of Ministers of the USSR of April 16, 1962. The creation of the rocket and the orbital block was entrusted to OKB-586 (now Yuzhnoye Design Bureau; Chief Designer M. K. Yangel), rocket engines - OKB-456 (now NPO Energomash; Chief Designer V. P. Glushko), control system - NII-692 (now KB "Khartron"; Chief Designer V. G. Sergeev), command instruments - NII-944 (now NIIKP; Chief Designer V. I. Kuznetsov). The combat launch complex was developed at KBSM under the leadership of Chief Designer E. G. Rudyak.

Orbital rockets compared with ballistic provide the following benefits:

unlimited flight range, which allows hitting targets inaccessible to ballistic intercontinental missiles;
the possibility of hitting the same target from two mutually opposite directions, which forces a potential adversary to create missile defense from at least two directions and spend much more money. For example, the defensive line from the northern direction - "Safeguard", cost the US tens of billions of dollars;
shorter flight time of the orbital warhead in comparison with the flight time of the warhead of ballistic missiles (when launching an orbital rocket in the shortest direction);
the impossibility of predicting the area where the warhead of the warhead will fall when moving in the orbital sector;
the possibility of ensuring satisfactory accuracy of hitting the target at very long launch ranges;
the ability to effectively overcome the existing anti-missile defense of the enemy.

The first and only regiment with 8K69 orbital missiles took up combat duty on August 25, 1969 at NIIP-5. The regiment deployed 18 launchers.

Orbital missiles 8K69 were removed from combat duty in January 1983 in connection with the conclusion of the Strategic Arms Limitation Treaty (SALT-2), which stipulated a ban on such systems. Later, on the basis of the 8K69 rocket, the Cyclone family of launch vehicles was created.

NATO code - SS-9 Mod 3 "Scarp"; in the USA it also had the designation F-1-r.

Missile system - stationary, protected from ground nuclear explosion mine launchers (silos) and KP. Launcher- mine type "OS". The launch method is gas-dynamic from the silo. Rocket - intercontinental, orbital, liquid, two-stage, ampoule. The combat equipment of the rocket is an 8F021 orbital warhead (ORB) with a braking propulsion system (TDU), a control system, a warhead (BB) with a charge of 2.3 Mt and an OGCh radio protection system.

During the flight of an orbital rocket, the following are carried out:

Rocket reversal in flight to a given firing azimuth (in the angle range of +180°).
Separation of I and II steps.
Shutdown of engines of the second stage and separation of the controlled OGCh.
Continuation of the autonomous flight of the MS in the orbit of an artificial satellite of the Earth, control of the MS with the help of a system of calming, orientation and stabilization.
After separation of the RHF, correction of its angular position in such a way that by the time of the first activation of the RV-21 radio altimeter, the antenna axis was directed to the geoid.
After carrying out the correction of the HF, movement along the orbit with angles of attack of 0 degrees.
At the calculated time, the first measurement of the flight altitude.
Before the second measurement, braking altitude correction.
The second measurement of flight altitude.
Accelerated reversal of the MSG to the position of descent from orbit.
Before de-orbiting, hold for 180 s to work out the angular disturbances and to calm down the EHR.
Starting the brake propulsion system and separating the instrument compartment.
Turning off the brake control and separation (after 2-3 s) of the TDU compartment from the BB.

Such a flight pattern of an orbital rocket determines its main design features. These primarily include:

the presence of a brake stage designed to ensure the descent of the HF from orbit and equipped with its own propulsion system, automatic stabilization (gyrohorizon, gyroverticant) and range control automatic, issuing a command to turn off the TDU;
original brake engine 8D612 (designed by Yuzhnoye Design Bureau), which runs on the main components of rocket fuel;
flight range control by varying the second stage engines shutdown time and TDU launch time;
installation of a radio altimeter in the instrument compartment of the rocket, which performs a double measurement of the orbital height and outputs information to a calculating device to generate a correction for the TDU turn-on time.

Along with the above-mentioned rocket design has the following features:

the use of the corresponding stages of the 8K67 rocket as I and II stages of the rocket with minor design changes;
installation in the instrumental compartment of the rocket of the SUOS system, which ensures the orientation and stabilization of the warhead in the orbital section of the trajectory;
refueling and ampulization of the OGCh fuel compartment at a stationary refueling point in order to simplify the launch facility.

The change in the design of the I and II stages of the 8K67 ballistic missile when used as part of an orbital missile is reduced mainly to the following:

instead of a single instrument compartment, an instrument compartment with reduced dimensions and an adapter are installed on the orbital rocket, in which the control system equipment is located. After launching into the calculated orbit, the instrument compartment with the control system equipment located in it is separated from the body and, together with the RC, makes an orbital flight until the launch of the brake engine 8D612 of the RC control module;
in the tail section of the second stage of the rocket, containers with decoys and anti-missile defense systems are not installed;
the composition and layout of the control system instruments was changed, a radio altimeter was additionally installed (Kashtan system).

According to the results of flight tests, the design of the rocket was finalized:

all connections of the refueling and draining supply lines of the rocket engines are made welded, with the exception of four connections of ampoule membrane plugs installed on the refueling and draining lines;
connections of pressurization gas generators of oxidizer tanks of I and II stages with tanks are welded;
filling and drain valves are installed on the bodies of the tail compartments of I and II stages;
the II stage fuel drain valve was cancelled;
flanges for detachable connections of membrane assemblies at the inlet to the HP of the main and steering engines are replaced by welded pipes or flanges for welding with pipelines;
in places of welding of units made of stainless steels with elements of tanks made of aluminum alloys, strong-tight bimetallic adapters made by stamping from a bimetallic sheet are used.

The conditions for the combat duty of the missile - the missile is on alert in the silo in a refueled state. Combat use- in any weather conditions at air temperatures from - 40 to + 50°C and wind speed near the earth's surface up to 25 m/s, before and after nuclear impact according to the DBK.

After carrying out fire bench tests and aircraft tests of the TDU OGCh under weightless conditions in December 1965, LKI of the 8K69 rocket began at the 5th NIIP.

During the LCI, 19 missiles were tested, including 4 missiles in the Kura region, 13 missiles in the Novaya Kazanka region, and 2 missiles in the Pacific Ocean. Of these, 4 emergency launches, mainly for production reasons. In launch N 17, the head of the 8F673 was rescued using a parachute system. Flight tests were completed on May 20, 1968.