Perimetr 15E601
During the Cold War, the Soviet Union employed several systems for providing assured communications of nuclear weapons release authority. The Perimetr system was designed to communicate retaliatory launch orders. The related "Dead Hand" system was an automated system to determine whether Russia was under nuclear attack. Although these two systems operated in tandem, and are frequently blurred together in Russian writings, they were in fact discrete capabilities. That is, Perimetr could be used to disseminate launch orders from sources other than "Dead Hand", which in turn had communications channels in addition to Perimetr.
The General Staff monitors the status of the weapons of the nuclear triad and will send the direct command to the launch crews following the president’s decision to use nuclear weapons. The Russians send this command over multiple C2 systems, which creates a redundant dissemination process to guarantee that they can launch their nuclear weapons. Moscow also maintains the Perimetr system, which is designed to ensure that a retaliatory launch can be ordered when Russia is under nuclear attack.
The development of a system of guaranteed retaliation began in the midst of the Cold War when it became clear that electronic warfare systems, which were being constantly improved, would soon be able to block the regular channels controlling the strategic nuclear forces. A backup method of communication was needed that would guarantee the commands would make it to the launchers. It was then that the idea was conceived to use a missile equipped with a powerful radio transmitter as a communication link. While flying over the Soviet Union, the missile would send the launch command not only to command centers of the strategic missile force, but also directly to the launchers.
After the order received from the upper command posts of the Strategic Missile Forces to a special command post, a 15P011 command missile with a special 15B99 head is launched. The U.S.A. deployed a similar system, the Emergency Rocket Communications System [ERCS].
At the beginning of the 1970s, taking into account the real possibilities of highly effective methods of radio electronic suppression by a potential enemy of the SMF combat control equipment, it became very urgent to ensure that combat orders were issued from the highest levels of command (the General Staff of the USSR Armed Forces, the Strategic Missile Forces) to command posts and individual strategic missile launchers , standing on alert, in case of emergency.
There was an idea to use for this purpose, in addition to the available communication channels, a special command missile equipped with a powerful radio transmitter, launched in a special period and submitting commands for the launch of all missiles on alert duty throughout the USSR.
The development of a special command missile system, known as the "Perimeter", was assigned to the Yuzhnoye Design Bureau by government decree No. 695-227 of August 30, 1974. As a basic missile, it was originally intended to use the MR-UR100 (15A15) missile, subsequently stopped on the MR-UR100 UTTK (15A16) missile. The missile developed in the part of the control system received the index 15A11.
In December 1975, A sketch of the command missile was executed. The rocket was equipped with a special head section, which had an index of 15B99, which included the original radio engineering system for the design of the OKB LPI. To ensure the conditions of its operation, the VF during the flight had to have a constant orientation in space. A special system for its calming, orientation and stabilization was developed with the use of cold compressed gas (given the experience of developing a remote control for the SHG "Mayak"), which significantly reduced the cost and timing of its creation and development. The production of the MIR 15B99 was organized by the NGO Strela in Orenburg.
After the groundwork of new technical solutions in 1979, LCI command rockets began. At NIIP-5, and sites 176 and 181, two experimental shaft silos were commissioned. In addition, a special command post was established at site 71, equipped with newly developed unique combat control equipment to provide remote control and launch of a command missile on orders coming from the upper levels of the Strategic Missile Forces. At a special technical position, a screened anechoic chamber was constructed in the body of the assembly, equipped with equipment for autonomous testing of the radio transmitter.
Flight tests of the rocket 15A11 were conducted under the guidance of the State Commission, headed by Lieutenant-General V. Korobushin, First Deputy Chief of the Main Staff of the Strategic Missile Forces. A total of 10 missiles were assigned for flight tests. In connection with the successful launches and the fulfillment of the assigned tasks, the State Commission found it possible to be satisfied with seven launches.
The first launch of the command missile 15A11 with the equivalent of a transmitter was successfully carried out on December 26, 1979. The complex coupling algorithms of all the systems participating in the launch were tested, the possibility of providing the missile with a predetermined flight trajectory of the GS 15B99 (the vertex of the trajectory at an altitude of about 4,000 km, the range of 4500 km), the operation of all service systems in the regular mode, confirmed the correctness of the adopted technical solutions. A total of 10 missiles were assigned for flight testing. In connection with successful launches and fulfillment of the tasks, the State Commission considered it possible to be satisfied with seven launches.
During the testing of the "Perimeter" system, real launches of 15A14, 15A16, 15A35 missiles from combat objects were carried out according to orders transferred to the SGB of 15B99 in flight. Previously, additional antennas were installed on the launchers of these missiles and new receiving devices were installed. All the PU and command posts of the Strategic Missile Forces subsequently underwent further development.
Along with the flight tests, a ground check was performed on the working capacity of the whole complex under the impact of the damaging factors of the nuclear explosion at the training ground of the Kharkov Institute of Physics and Technology, in the testing laboratories of VNIIEF (Arzamas), at the Novaya Zemlya nuclear test site. The tests carried out confirmed the efficiency of the SS and MSS equipment at levels of impact of the nuclear explosion exceeding those specified in the TTT MO.
Even in the course of flight tests, the government decree set the task of expanding the functions to be performed by the command missile complex with the delivery of combat orders not only to the Strategic Missile Forces, but also strategic missile submarines, long-range and sea-launched missile aircraft at airfields and in air, control of the Strategic Missile Forces, the Air Force and the Navy.
LCI command rockets were completed in March 1982. In November 1984, the command missile was launched from Polotsk and gave a command to the silo launch facility of an RS-20 ICBM (SS-18 Satan) at Baikonur. The Satan was launched, and after each stage was tested, it was confirmed the warhead landed on the correct quadrant at the Kura test range on Kamchatka peninsula.
In January 1985, Perimeter was commissioned. Since then the system had been updated several times, with more modern ICBM missiles used as the command missile.
Many enterprises and organizations of various ministries and departments took part in the creation of the complex. The main of them are NPO Impulse (V.Melnik), NPO AP (n.A.Pilyugin), KBSM (AFUtkin), TsKBTM (BR.Aksyutin), MNIIRS (A.P. Bilenko), VNIIS (B.Ya. Osipov), Central Design Bureau "Geofizika" (GF Ignatiev), Research Institute-4 MO (EB Volkov).
In December 1990, in the 8th Missile Division (Village Yurya) on combat duty atonement Regiment (commander - Colonel SI Arzamastsev) with an upgraded command missile system, dubbed "Perimeter-RC", which includes a command missile, created on the basis of ICBM RT-2PM "Topol".
For more than 10 years, the command missile complex successfully fulfilled its important role in the defense of the state. As part of the START I agreement of June 1995, the command missile complex was withdrawn from combat duty. The command missile complex 15P011 with the 15A11 missile (based on the UR-100 MR) was on alert until June 1995, when the complex was withdrawn from combat duty as part of the START-1 agreement. According to other sources, this happened on September 1, 1995, when the 510th rocket regiment, armed with command missiles, was withdrawn from duty and disbanded in the 7th Missile Division (town of Vypolzovo). This event coincided in time with the completion of the withdrawal of the missile MR UR-100 from the combat missile of the Strategic Missile Forces and the re-equipment of the 7th rd, which began in December 1994, to the mobile ground-based missile system Topol.
The command missile "Perimeter" in the Strategic Missile Forces was later replaced by new systems of a similar purpose - PKP "Barrier", PKP "Granit". For the new Topol complexes, mobile and stationary command posts were developed. The mobile command post for the combat control of the Topol ICBM placed on the basis of a four-axle vehicle MAZ-543M. For fire control, the Barrier and Granit mobile command posts equipped with a missile were also used, with a transmitter instead of a payload, which, after the missile was launched, duplicated the start command for launchers located in positional areas.
On April 28, 1987, a missile regiment armed with Topol complexes with a Barrier mobile command post took up combat duty near Nizhny Tagil. PKP "Barrier" has a multiply protected redundant radio command system. A combat control missile is placed on the mobile launcher PKP "Barrier". After the rocket is launched, its transmitter gives the command to launch the ICBM.
15P656 / 15J56 / Gorn / Horn
Tests of the most advanced version of the Perimeter with the 15Yu75 missile (sometimes called 15Zh75) based on the first version of the intercontinental Topol began in 1990. All 4 missiles, having been launched ["started"] from Plesetsk, successfully completed their tasks. The earlier part of the "perimeter" system, along with missiles 15A11 missiles, were team-based with IRBM "Pioneer". Such a mobile complex with "Pioneer" command missiles was called "Horn". The index of the complex is 15P656, the rockets are 15J56.
It is known, at least, about one unit of the Strategic Missile Forces, which was armed with the Horn complex - the 249th rocket regiment stationed in the town of Polotsk, Vitebsk region, the 32nd missile division (Postavy), from March to April 1986 to 1988 stood on alert with a mobile complex of command missiles.
It is worth noting that there is information in the press about several types of missiles that were used or could be used to create the system. It is also known that tests of the most advanced version of the Perimeter with the 15Yu75 missile (sometimes called 15Zh75) based on the first version of the intercontinental Topol began in 1990. All 4 missiles, having been launched from Plesetsk, successfully completed their tasks. But a dark time had come in the history of Russia: the government of Yeltsin stopped the development of this program and, according to a number of military sources, Perimeter was removed from combat duty for some time.
After the start of the restoration of the armed forces under Putin and the resumption of funding for the Strategic Missile Forces in the required volume in the 2000s, general information about the Perimeter system first appeared. In 2011, information was officially announced about the presence of a command missile system on combat duty of the Russian strategic nuclear forces. In 2016, a successful test launch of the 15Yu75 rocket was carried out in Plesetsk to test the system's performance.
When in December 2011, the commander of the Strategic Missile Forces Sergei Karakaev visited the KP, he was asked about it. He replied: "Perimeter" exists. The system is on alert duty. If there is a need for a retaliatory strike, when it is impossible to bring a signal to the part of the launchers, this command can come from these missiles from the Perimeter ..."
15Yu75 Sirena-M / Siren
In the immediate plans of the Russian Ministry of Defense for the purchase of strategic nuclear missile weapons announced at the end of 2019, the already well-known intercontinental ballistic Yars, promising heavy ICBMs Sarmat and the Sirena-M command rocket [komandnya raketu] complex were named . The latter was practically unknown. On June 10, 2021, the first test launch of a new command missile of the Sirena-M command missile system, based on the missile of the Yars-M complex, was carried out from Plesetsk.
The terms “command missile system” and “command missile” refer to the legendary late Soviet development known as the Perimeter system. In the United States, for obvious reasons, it is called the "Dead Hand" (Dead Hand). The topic is really terrible and belongs to the most critical situation, if completely distraught opponents decide to launch a massive strike with ballistic missiles with nuclear warheads on the territory of our country, mistakenly believing that they can destroy Russia without retaliatory consequences for their territory. Considering the possibility of such a scenario, at the end of the USSR they created the 15P175 Sirena command missile system.
The enemy, who has decided to destroy Russian control centers, the capital, the army headquarters and the strategic weapons bases known to him with a global strike, will in fact activate the "Perimeter". According to open specialized publications, in the event of a long-term lack of communication with a number of command structures of the army and strategic missile forces, the system was supposed to launch a command missile, which in flight would broadcast a signal about a retaliatory strike against the aggressor with all available missiles. The “destroyed” country was thus guaranteed to send the aggressor state to the next world, and in a nuclear war there was not even a hint of the possibility of victory for one of the parties.
It is worth noting that there is information in the press about several types of missiles that were used or could be used to create the system. It is also known that tests of the most advanced version of the Perimeter with the 15Yu75 missile (sometimes called 15Zh75) based on the first version of the intercontinental Topol began in 1990. All 4 missiles, having been launched Plesetsk, successfully completed their tasks.But a dark time had come in the history of Russia: the government of Yeltsin stopped the development of this program and, according to a number of military sources, Perimeter was removed from combat duty for some time.
After the start of the restoration of the armed forces under Putin and the resumption of funding for the Strategic Missile Forces in the required volume in the 2000s, general information about the Perimeter system first appeared. In 2011, information was officially announced about the presence of a command missile system on combat duty of the Russian strategic nuclear forces. In 2016, a successful test launch of the 15Yu75 rocket was carried out in Plesetsk to test the system's performance.
At the end of 2019, Russia announced the appearance of a new version and the Perimeter with the Sirena-M command missile system , which will enter service during 2020-2025. What characteristics the new missile has, of course, is not reported, but it is obvious that they shouldl be enough to cool off everyone who still dreams of destroying Russia with a missile attack.
On 28 December 2019 Deputy Defense Minister Alexei Krivoruchko stated the upgraded Sirena-M command missile system will be delivered to the Strategic Missile Forces (RVSN) by 2025. "Next year, we plan to conclude another three-year contract for the manufacture of Yars mobile complexes for the rearmament of three more missile regiments, as well as for the manufacture of the Sirena-M mobile command missile system with their delivery until 2025," he said. in an interview with the Krasnaya Zvezda newspaper . Command missiles are designed to transmit combat control signals for the launch of Strategic Missile Forces missiles in the event of a massive nuclear missile attack by the enemy, which is why they were called "doomsday" missiles in the press. According to Krivoruchko, the implementation of these measures will make it possible this year to reach 76% of the units of the Strategic Missile Forces with modern weapons, and by 2022 to increase this level to 92%. At the same time, in 2020 it is planned to complete the main volume of ground experimental testing and start flight tests of the Sarmat missile system.
Boris Lagutin was born in 1927. After graduating from the Bauman Moscow State Technical University in 1949, he was sent to work in the apparatus of the USSR Ministry of Defense Industry. However, he did not leave his scientific activity and continued to do postgraduate studies at his native university. In 1956 he successfully defended his PhD thesis.
In the early 1960s, Lagutin was sent to NII-1 MOP, headed by Alexander Nadiradze. Here he leads the design department, then a special design bureau, while also being deputy director for science and design. In 1987, Lagutin was appointed general designer - director of the Moscow Institute of Thermal Engineering. For more than thirty-five years before retiring, Boris Lagutin was engaged in the development of mobile ground-based missile systems with solid-propellant guided ballistic missiles.
"Tselina-2"
A government decree on the development of a single missile for silo ["mine"], rail and ground-based types was issued on August 9, 1983. The development of a project for a combat ground-based missile system with a three-stage solid-propellant intercontinental ballistic missile with a MIRV was started at Yuzhnoye Design Bureau under the leadership of Vladimir Utkin.
The project provided for the placement of an ICBM launcher on a twelve-axle wheeled tractor MAZ-7906. The twelve-axle rocket carrier was supposed to consist of two articulated six-axle tractors. It was supposed to place on the launcher a three-stage ICBM articulated from two blocks. The docking of the blocks was to be carried out before the launch of the rocket.
The development of the project was terminated.
Work in the Soviet Union on the creation of a mobile ground-based missile system with a solid-propellant ICBM began in the late 1960s. Initially, light solid-propellant ICBMs with a launch weight of up to 50 tons were used to place on ground mobile launchers. Since the beginning of the 1970s, work has continued towards the creation of a complex with a RT-23 missile weighing 80-90 tons, initially with a monoblock combat equipment, and then with an individually targetable multiple warhead, the mass of the rocket increased to 105 tons.
It was decided to have several dispersed stationary launchers for each missile in the complex and to transport missiles to them covertly by ground transporters. In the first studies on the creation of a vehicle for the RT-23 rocket, a caterpillar articulated chassis was considered.
In 1976, KB-3 of the Kirov Plant, under the leadership of chief designer N.S. Popov, created prototypes of the tracked articulated chassis “object 829”, consisting of four sections, based on road wheels and tracks of the T-80 tank. The weight of such a chassis was about 200 tons. For the first time, samples of the tracked articulated chassis "object 829" were proposed for the self-propelled launcher of the Temp-2S PGRK.
For this PGRK, the possibility of using the SPU of the RT-20P complex was also considered. In the conclusion of VNII-100, it was said that the creation of a tracked chassis weighing less than 65 tons for a new complex. impossible. For further work, a four-track chassis with a total weight of about 70 tons was proposed.
The preliminary design of "Temp-2S" was completed in early 1968. According to the results of consideration of the preliminary design in accordance with the Decree of the Central Committee of the CPSU and the Council of Ministers of the USSR of May 24, 1968. No. 374-142, the institute staff was tasked with developing a working draft of a solid-propellant rocket and a mobile soil complex in two versions - on a wheeled and tracked chassis. At the same time, the weight of the SPU was limited to the 60th and 70th tons, respectively.
SPU on caterpillars - 15U67 or "object 829" was developed by KB-3 of the Leningrad Kirov Plant (LKZ), and SPU 15U68 on the wheelbase of a special six-axle MAZ-547A vehicle was developed at the Special Design Bureau of the Minsk Automobile Plant. By 1970, prototypes of a caterpillar SPU were developed and assembled. However, the leadership of NII-1 rejected the projects of tracked SPUs, rightly believing that the missile control devices would not be able to withstand the vibration created by the tank chassis. Preference was given to the wheeled chassis of the Minsk Automobile Plant, on the basis of which a five-axle, and then a six-axle wheeled chassis MAZ-547 was created, capable of transporting a load of a given mass off-road.
When creating the first mobile complexes, no one really thought (as well as when creating other weapon systems) about the life support of the service personnel. The fact that people need to sleep and eat, that they need to be protected, P. Tyurin and M. Yangel, who created the first mobile complexes, either did not think, or believed that this was the business of the military. "Temp-2S" became the first missile system to provide truly mobile autonomous operation during combat patrols.
Due to the complexity of the operation of such a chassis, it was later abandoned and began to create wheeled vehicles.
As part of the work on rocket and space topics, in 1979 the Decree of the Central Committee of the CPSU and the Council of Ministers of the USSR was issued on the development of a wheeled special conveyor with a carrying capacity of 220 tons by SKB MAZ.
With the transition of the combat railway missile and mine complexes to the modernized RT-23UTTKh missile, RT-23UTTKh (15Zh62) ICBMs began to be placed in the soil complex. The Tselina-2 soil complex missile is similar to the RT-23UTTKh missile, since, according to the Decree of the Central Committee of the CPSU and the Council of Ministers of the USSR of August 9, 1983, the development of missile systems with the unified RT-23UTTKh Molodets missile in three types of basing was given: military railway; mobile soil and mine. The rocket used the main technical solutions worked out on the 15Zh52 rocket. The Moscow Institute of Thermal Engineering (MIT), headed by A.D. Nadiradze, was appointed as the head organization for the mobile ground rocket "Tselena-2". The development of the rocket for the Tselena-2 complex remained with the Yuzhnoye design bureau, general designer V.F. Utkin.
Government Decree No. 768-247 on the creation of the RT-23 UTTKh missile system with a single missile for three types of basing (mobile - rail and ground, stationary - mine high security) was issued on August 9, 1983, and in November of the same year, by a joint decision of the Ministry of Defense , the Ministry of General Machinery, the Ministry of Defense Industry and the Ministry of Medium Machinery are specifying the timing of the creation of a single missile. In April 1984, the Ministry of Defense issued updated technical specifications to the developers of complexes based on RT-23UTTKh missiles, which have already unambiguously determined that a single missile is being developed taking into account individual design and circuit differences due to the peculiarities of operation and combat use as part of mobile and stationary complexes.
A strategy was adopted for the development of complexes and missiles for them, which was proposed by the CY: first of all, they should be developed taking into account tight deadlines - (the start of mass production since 1986) a rocket for the BZHRK 15Zh961 and a rocket for the soil complex 15Zh62. The missiles use the basic technical solutions worked out on the 15Zh52 missile, the resistance of the missile design to the damaging factors of nuclear weapons is ensured at a level that is optimal for mobile launches. By the Decree of the Government, the BZHRK with the 15Zh961 missile was adopted by the Soviet Army in November 1989. By this time, a significant part of the grouping had already been put on combat duty in positional areas. As for the soil mobile complex being developed by MIT with the 15Zh62 missile (the theme "Tselina-2") and the MZKT-7906 twelve-axle tractor, its development was discontinued, as it became obvious that the rocket for stationary launch 15Zh60 is being developed based on the date of commencement of serial production (since 1987), should provide the upper level of resistance to PFYAV.
The development of a rocket for the 15Zh60 stationary complex was carried out after the rocket for the 15Zh961 railway complex, and it began with the release in the third quarter of 1984 by Yuzhnoye Design Bureau and related organizations of additional design materials, which are a draft design for a stationary mine complex with a rocket developed in relation to the requirements formulated by the Customer for a high-survivability fixed-based complex. At the end of 1984, the design materials were reviewed and approved by Minobshchemash and the Customer.
Since 1985, the cooperation, headed by the KBYu, began the deployment of a full-scale R & D to create the 15P060 complex. In the process of design work, the technical design of a silo-based missile was formed and went into further development - a solid-propellant light class ICBM with a launch weight of ~ 104.3 tons, delivering ten APs of the second level of resistance to designated targets, having an increased level of resistance to PFYAV; a combat missile system that ensures the launch of a missile without delay for the normalization of the external situation during multiple nuclear impact on neighboring DBK facilities and high-altitude nuclear blocking of the positional area, as well as with a minimum delay in case of non-damaging nuclear impact directly on the launcher.
The high performance of the 15Zh60 rocket to ensure an increased level of resistance to PFYAV was achieved due to: the use of a newly developed protective coating applied to the outer surface of the rocket body and providing comprehensive protection against PFYAV application of CS developed on the element base with increased durability and reliability application of a special coating with a high content of rare earth elements to the case of the sealed instrument compartment, which housed the control system equipment the use of shielding and special methods of laying the onboard cable network of the rocket introduction of a special program maneuver of the rocket during the passage of a cloud of ground-based nuclear weapons
Flight tests of the 15Zh60 rocket were carried out at the Plesetsk training ground. Four launchers (Yuzhnaya-1, Yuzhnaya-2, Svetlaya-1 and Svetlaya-2) were built at the test site for flight tests. The location of these launchers was chosen in such a way as to ensure the use of dedicated fall areas for the first stages when firing at any range. The Yuzhnaya-1 and Yuzhnaya-2 sites were put into operation in 1986, Svetlaya-2 in 1987 and Svetlaya-1 in 1988. Launch sites were used for missile launches. South-1", "South-2" and "Light-2". No launches were carried out from the Svetlaya-1 launch pad; it was used to test individual elements of the complex according to special programs.
The first rocket launch on July 31, 1986 from the Yuzhnaya-1 site was successful. The launch of the 2L rocket was an emergency; the cause of the accident is the failure of the control system at the initial section of the movement. The launch of the 5L rocket is also emergency due to the failure of the onboard control system. In order to eliminate the reasons that caused the failures of the control system, the developer carried out its modifications, the effectiveness of which was fully confirmed by additional ground testing on the integrated stand and subsequent launches. The launch of 4L also became an emergency - the liner of the nozzle block of the propulsion system of the first stage collapsed. As a result of a thorough analysis, the cause of the failure was identified and the nozzle block was refined.
A lot of work done by the development organizations brought positive results - there were no more accidents during launches of 15ZH60 missiles. The final launch under the test program was held on September 26, 1988. In total, 16 missiles were launched during state joint flight tests. Based on the results of the GSLI, a report was issued by the State Commission with a recommendation to adopt the complex into service. The last launch of the 15Zh60 ICBM - the 8L rocket that passed the transport tests - was carried out on November 1, 1989 in the "Aquatoria" area with a positive result. It entered the statistics as a test launch of a batch rocket carried out from the Svetlaya-2 launcher.
On experimental combat duty, the first ICBMs were put on August 19, 1988 in the 46th Nizhnedneprovskaya Red Banner Order of the October Revolution missile division (Pervomaisk, Nikolaev region, Ukrainian SSR). Deployment proceeded at a rapid pace - by the end of the year, 20 missiles were already on combat duty. It can be considered an outstanding achievement that, with an initial development lag of 10 years or more, the 15Zh60 ICBM was put on combat duty less than two years behind the American MX ICBM (LGM-118A).
In 1989, the deployment in the first positional area was continued, in the same year, the deployment of a new ICBM in the second positional area was started - in the 60th Taman Red Banner Order of the October Revolution Missile Division named after the 60th anniversary of the USSR (Tatishchevo, Saratov Region, RSFSR). The new missile replaced the UR-100N UTTKh (15A35) ICBMs in both deployment areas. November 28, 1989 the complex was adopted by the Soviet Army. By the end of 1989, 56 missiles had already been deployed in both position areas (46 in the 46th and 10 in the 60th divisions).
However, starting from 1990, despite the fact that at least 8 missiles were manufactured at the PMZ and prepared for shipment to positional areas, the deployment of ICBMs was stopped - the leadership of the USSR adopted a new defense doctrine. In July 1991, the START-1 treaty was signed, and by November 1991, the process of the collapse of the USSR had actually become irreversible. After the formal collapse of the USSR in December 1991, the production of new ICBMs at the PMZ was completely stopped, the missiles deployed on the territory of Ukraine were subject to decommissioning and destruction under international treaties. In 1993-1994, all ICBMs on the territory of Ukraine were removed from combat duty, and the APs removed from the missiles were then taken to Russia for disposal.
In 1998-2001, the second stage was carried out - all 46 "Ukrainian" 15Zh60 ICBMs were removed from OS silos. In 1999-2002, all ICBMs (including those that were never put on combat duty) were dismantled and disposed of. OS silos were blown up except for one serving for museum purposes.
The life cycle of ICBMs deployed on the territory of the Russian Federation was also short-lived - it was decided to refuse to extend (following the example of ICBM 15Zh961) the warranty period to 15 years, and by the end of 2001 all 10 ICBMs were removed from the silo and sent for disposal. After modernization with the designation 15P765-60, the newest ICBMs RT-2PM2 "Topol-M" (15Zh65) were deployed in the OS silo. "Vis-a-vis" ICBM 15ZH60 - American ICBM MX - was also withdrawn from service in 2002-2005.
Assessing the DBK 15P160, it can be noted that for the first time in domestic practice, a highly efficient fourth-generation stationary missile system was developed with the latest solid-propellant ICBM equipped with a MIRV with 10 AP, providing a guaranteed retaliatory strike, including in conditions of direct nuclear impact on the positional district.
In the west, the 15Zh60 missile received the designation SS-24 "Scalpel" Mod 2. The name according to START-1 is RS-22B.
The separation of the head fairing was carried out after passing through the zone of high-altitude blocking nuclear explosives. On the 15Zh60 rocket, the schematic and design solutions worked out on the 15Zh44 and 15Zh52 missiles for controlling the flight of the II and III stages by the deflection of the head compartment, the mortar separation of the stages, the separation of the combat stage and the breeding of the elements of combat equipment were retained. The mortar separation of the stages was provided by pressurization with gas from the powder pressure accumulator of the interstage volume and the transverse division of the connecting compartment with an elongated shaped charge. This design guaranteed shock-free separation of the stages and ensured the maximum density of the layout of the interstage part of the rocket.
Propulsion systems (PS) of the rocket were developed mainly within the framework of cooperation that developed at the stage of creating complexes with 15Zh44 and 15Zh52 missiles. 15Zh60 solid propellant rocket propellant rockets (second level of resistance) are designed to meet the increased requirements for power-to-weight ratio, control forces (15D305, DU-I) and the degree of protection against PFYAV (15D339, DU-II; 15D291, DU-III). For MBR 15Zh60 and 15Zh961 engines, fuels of the third and fourth generations based on the new ADNA chlorine-free oxidizer have been developed. The complex of fundamental works on the creation and implementation of ADNA as one of the energy-intensive and environmentally friendly oxidizers, carried out in collaboration with the institutes of the Academy of Sciences, higher education and industry institutes, was a major domestic scientific and technical achievement, more than 20 years ahead of the world level in the field of rocket fuel energy. For the first time, a fundamentally new highly efficient fuel, aluminum hydride, was used in the fuel formulation of these rockets.
In the course of work on the creation of sustainer solid propellant rocket engines MBR 15Zh60 and 15Zh961, new structural, heat-shielding and erosion-resistant materials were developed, including high-strength organic and high-modulus carbon fibers, carbon compositions with a 2- and 3-dimensional oriented matrix, high-strength heat-resistant adhesives, and the technology manufacturing and methods of non-destructive quality control, new fuels with unique energy and operational characteristics and optimal forms of charges based on them have been created. For the first time in domestic practice, the casings of the propulsion system were developed from the SVM organic material, which has a high specific strength, which contributed to the improvement of the energy-mass perfection of rockets.
This made it possible to create and implement for use: engine cases made of organoplastic "cocoon" design critical section parts and sockets of nozzle blocks made of carbon-carbon materials large-sized multi-block liner made of three-dimensionally reinforced carbon-carbon material carbon-carbon nozzles swivel control nozzle based on elastic hinge tail compartment made of structural carbon fiber.
The first stage consisted of a sustainer solid propellant rocket engine 15D305, tail and connecting compartments. In a fundamentally new engine of the 1st stage developed by the KBYu and produced by the PMZ, a higher-energy (compared to the 15Zh961 MBR) mixed solid propellant of the "OPAL" type was used - the developer of the LNPO "Soyuz". the solid propellant charge had a star-shaped channel and was firmly attached to the engine housing. The thrust characteristics were boosted by 30% compared to the 15D206 engine of the first stage of the 15Zh961 rocket, which led to an increase in pressure in the combustion chamber up to 100 kgf / cm2, and also used as a thrust vector control central, partially recessed into the combustion chamber, multi-position (circular diagram of the creation of the control force Rupr.
The body of the step is a one-piece organoplastic "cocoon" type, made by winding threads from a composite material selected according to the then state of the domestic production base. Taking into account the provision of the minimum mass of the structure, the following option was chosen: at the base, a bundle of threads made of a composite material and a special binder. On the second and third march steps, the same version of the hull manufacturing was used. For roll control in the DU-I work area, 4 aerodynamic rudders installed on the outer surface of the head fairing were used. In addition, at the end of the work section of the first sustainer stage, the stage was also controlled by the deflection of the rocket head.
The engines of the second and third stages were each equipped with a central stationary nozzle partially recessed into the combustion chamber with a telescopic movable socket nozzle made of carbon-carbon material, which made it possible to increase the degree of expansion of the nozzle and, accordingly, the specific impulse, without increasing the overall dimensions of the rocket.
The second stage consisted of a sustainer solid propellant rocket engine 15D339 and a connecting compartment. The body of the second stage is a one-piece organoplastic "cocoon" type. Fuel of the second stage - solid mixed type "START" (developer LNPO "Soyuz"). Solid propellant charge - firmly fastened to the engine housing, with a cylindrical-conical channel with an inclined annular groove of the "umbrella" type.
A special multifunctional coating was additionally applied to the body of the DU-II developed by the KYU and manufactured by the PMZ rocket 15Zh60 (compared to 15Zh961). The control of the second stage was carried out by deflection of the warhead and aerodynamic rudders (in roll) mounted on the nose fairing.
The third stage consisted of a sustainer solid propellant rocket engine 15D291 and a transitional compartment. The DU-III missiles 15Zh60 and 15Zh961 developed by the Iskra Design Bureau and manufactured by the Perm Chemical Equipment Plant are almost identical (mixed solid propellant of the AP-65 type, developed by LNPO Soyuz). The body of the DU-III missile 15Zh60 (compared to the DU-III missile 15Zh961) is additionally coated with a special multifunctional coating. The body of the third stage is a one-piece organoplastic "cocoon" type. The control of the third stage was carried out by the deflection of the head part and the roll solid propellant rocket motors of the stage.
For the 15ZH60 missile, a new warhead of increased resistance to PFYAV 15F14 with warheads of increased specific power and having characteristics close to the Mk21 warhead of the "MX" missile was developed. The MIRV is equipped with ten high-speed BB 15F174 of an increased power class of at least 0.8 Mt each. The warhead is of a separable type of individual guidance with ten thermonuclear warheads with a capacity of 0.43 Mt and a complex of anti-missile defense systems developed by the KBYu. Initially, the KSP PRO was manufactured at the Yuzhmash Production Association, but since May 1986, production has been transferred to related enterprises of the RSFSR.
The stage of disengagement of warheads - "pushing" scheme, the placement of warheads in one tier, the stage engine - LRE RD-866 (15D264), created in KB-4 KBYu and produced at Yuzhmash, which worked on liquid high-boiling, stable, long-term self-igniting components fuels: unsymmetrical dimethylhydrazine (UDMH) and nitrogen tetroxide (AT).
The RD-866 engine is multifunctional, without generator gas afterburning, with repeated switching on of the BT (high thrust) and MT (low thrust) LRE, provided multiple starting and thrust control. The engine worked according to a combined scheme (displacement and pump supply of fuel components). Provided a wide range of changes in costs and pressures for consumer mechanisms. RD-866 contained: a centralized power source (consisting of two turbopump units with gas generators and two feeders); single-chamber LRE BT; 16 LRE MT.
For the 15Zh60 three-stage solid-propellant rocket, the "breeding" [ie, MIRV bus] stage was required not only to ensure the formation of battle formations from APs and means of overcoming missile defense, but also to use the "effective overclocking" mode to achieve the specified maximum firing range - ensuring the operation of the breeding stage in the active part of the trajectory as the fourth stage of the rocket , which provided a significant gain in payload mass (up to 15%). To reduce the length of the rocket, a variable geometry head aerodynamic fairing was used, covering the warhead, the two wings of which were closed after the rocket left the TPK.
The structure of the rocket was protected by a special external multi-functional coating along the entire length of the rocket (including the nose fairing) to protect against damaging effects.
A very important moment in the process of creating missiles 15Zh961 and 15Zh60 with the required level of basic characteristics was the development of control systems for them, to which the Customer imposed very strict requirements in terms of the level of basic flight performance - combat readiness, hit accuracy, resistance to the effects of PFYAV in conditions repeated impact on the positional area and its high-altitude blocking by nuclear explosions, increased resource of continuous operation of onboard equipment.
The fulfillment of these requirements required the developers of the control system to create command gyroscopic instruments with improved accuracy characteristics, a new BTsVK "Biser-3" with increased productivity and resistance to the effects of damaging factors of nuclear weapons, ensuring aiming by implementing an autonomous determination of the azimuth of the control element installed on a gyro-stabilized platform, with using a ground-based set of command instruments located on the TPK. Within the framework of a special program for the control system, a radiation-resistant element base and large integrated circuits for the onboard computer center were developed.
The creation of special radiation-resistant electronics for ICBMs in the USSR was a complex process that began back in the 60s - the decision No. 149 of the Military Industrial Commission on the resistance of electrical radio elements to the damaging factors of a nuclear explosion was adopted in 1968.
In the future, hard work in this direction did not stop - for example, only during 1977-1979. under a special program, 6 test nuclear explosions were carried out at Soviet test sites, which made it possible to obtain valuable data on the radiation resistance of the electronic components of the systems of the main Soviet ICBMs; made it possible to study the effect of hard gamma radiation and neutron fluxes on the hulls, warheads and electronics of Soviet ICBMs, including advanced ones; made it possible to study the effects of exposure to powerful electromagnetic pulses and the radiation resistance of various electronic components of the control systems of Soviet ICBMs.
The results of tests and theoretical studies carried out for a long time led to the conclusion that the weakest link in the design of ICBMs when exposed to PFYAVs is the electronic systems themselves, the resistance of which to the damaging factors of nuclear explosions was recognized as unsatisfactory in the perspective of the emergence of new high-precision delivery vehicles. nuclear munitions and nuclear munitions of a new generation in the countries-probable adversaries (primarily the United States) in the 80s. As a result, in 1982, a special resolution of the military-industrial complex was issued on the creation of electronic elements resistant to PFYAV - from very large integrated circuits to transistors and capacitors. More than 600 organizations were involved in the work - research institutes, design bureaus, universities. In 1985, at one of the meetings of the military-industrial complex, it was stated that electronic products,
A feature of the SU was the solution of a number of new tasks: restoring information in the computer after exposure to PFYaV by rewriting it to the RAM from the information store on a magnetic disk implementation of terminal guidance principles use of an element base of increased resistance to PFYAV (for 15Zh961 - level I, for 15Zh60 - level II) Combat duty of 15Zh60 missiles with command devices constantly engaged interfacing with the SBU system "Signal-A"
The control system of the second level of resistance was developed by NPO "Khartron" (chief designer V.G. Sergeev, then Ya.E. Aizenberg). The control system introduced circuit-algorithmic protection of the control system equipment from gamma radiation during nuclear explosions. Design Bureau "Yuzhnoye" in cooperation with TsNIIMash, the Institute of Technical Mechanics of the Academy of Sciences of the Ukrainian SSR, Dnepropetrovsk State University developed a dynamic scheme of the system with variable masses and configuration (including abruptly changing), taking into account the elasticity of the body and cardan assembly, which was the basis for the development control systems. The new method of control - the deflection of the warhead - was fraught with great potential, which were fully realized. This method did not require the expenditure of rocket energy due to the loss of propulsion engine thrust during the creation of the actual control forces. Due to this, disturbances in the roll channel were minimal,
In 1983, the Minsk Automobile Plant (MAZ) produced a prototype wheeled special transporter "7904", which in the same year was sent to NIIP-5 (Baikonur) for testing. The machine was intended for use in the Energia-Buran rocket and space system for delivering spent launch vehicle side stages that fell to the ground to the cosmodrome and as a chassis for the missile system.
On the chassis "7904", 6.8 meters wide, a 1500 hp marine engine, two parallel hydromechanical transmissions, 12 drive wheels with a diameter of 3 meters were installed. Management was carried out by swivel front and rear wheels. The chassis could only be used in desert areas. Due to the easy detection of such a machine by space means, it was proposed to create a chassis for movement in the central zone of the Soviet Union, in a wooded area. The operation of the "7904" chassis made it possible to accumulate the necessary experience, which was later used to create vehicles for a ground combat mobile missile system.
For the Tselina-2 complex, two variants of the MAZ-7906 and MAZ-7907 chassis were created at the SKB MAZ. In the early 1980s, both variants of the chassis of an unpaved transport unit with a carrying capacity of up to 140-150 tons were tested. MAZ-7906 had a hydromechanical transmission, a 1500 hp diesel engine. and wheel formula 16x16. The MAZ-7907 chassis of the unpaved launcher of the Tselina-2 complex MAZ-7907 had 12 axles and all the wheels were driven, front and rear - steered.
An AC electric transmission and a 1200 hp gas turbine engine were installed on the "7907" chassis. The turning radius of the car turned out to be less than the length of the car. The car was designed for operation with mounted equipment in off-road conditions and it was successfully tested. Chassis "7907" and "7906" were intended for transporting missiles to the launch site, which were supposed to be built for one missile. Due to the complexity of operation, the mobile soil complex was not adopted for service. In 1996, MAZ-7907 was used to transport a boat 40 meters long and weighing 100 tons from Borisov to Lake Naroch.
R-36?3 / 15?18?2 Icarus
The project of an intercontinental ballistic missile of a heavy class. The rocket was developed in the early 1990s at Yuzhnoye Design Bureau. Chief designer - Stanislav Us. Work on the project began after the completion of the development of the ICBM "Voevoda" R-36M2. It was envisaged to create a MIRV ["multiply charged"] ICBM of a heavy class.
The preliminary design of the rocket and the complex was developed at the Yuzhnoye Design Bureau (Dnepropetrovsk, Ukraine) under the guidance of Academician of the USSR Academy of Sciences V.F. Utkin in 1991. Work on the project was terminated in 1991-1992. In some sources, SALT-2 negotiations are cited as the reason for the termination of development, but most likely there were several reasons. It is also impossible not to take into account a certain nationalization of the development of ICBMs for the Russian Strategic Missile Forces. The fate of the preliminary project materials is not known yet -the materials were transferred to the Strategic Missile Forces - as well as the 1L copy of the 15Zh65 Topol-M / Universal ICBM. In addition, Yuzhnoye Design Bureau was extremely interested in continuing work with such a customer as the Strategic Missile Forces. So far, the history of all the key moments of that demarcation of the Yuzhnoye Design Bureau with the general customer has not been disclosed. In the second half of the 1980s, the West wrote about the new heavy ICBM under the code SS-X-26. As it is now clear, it was about satellite (apparently) images of the R-36M2 and the first emergency test launches. They were written about in the Western press. About "Icarus" apparently only some rumors leaked there, because in 1992 someone wrote about the ongoing development on the topic of SS-X-26. Then SS-X-26 was somehow imperceptibly reclassified as SS-18 mod.5 and mod.6, and the SS-X-26 index went to the Courier ICBM (previously having the index SS-X-27). "Topol-M", which entered the test in 1994, received the index SS-X-27, although there was a time when we thought that it would be SS-25 modX. In general, both in the 1980s and in the 1990s there was some confusion in the identification of missiles the USSR currently had in development, In some literature, the index 15A18M2 is erroneously attributed to the R-36M2 missile . Also, the index 15A19 is sometimes mistakenly attributed to the Icarus project. taking into account the weights of the sources, as well as taking into account the fact that 15A19 is identified in most sources as a variant of the R-36M2 equipped with guided warheads, it remains 15A18M2. Why not M3? Because the names "R-36M", etc. there was no commonality of sub-indices with 15A18M, etc.
R-36M = 15A14 R-36MUTTH = 15A18 R-36M2 = 15A18M R-36M3 = 15A18M2Another point - some sources mention the R-36M2UTTH / 15A18M2 ICBM. Moreover, most often this index is mentioned in full context with the usual "Satan" / "Voevoda", and not in view of some exotic or just modification. On this basis, some conclude that the R-36M2UTTH index is fictitious. No data is available on the design - but it can be assumed that the design of the rocket was based on the 15A18M ICBM. Control system - autonomous inertial control system using a computer. Presumably, the design bureau "Khartron" (Kharkov, Ukraine) was to become the developer of the control system. The propulsion system is a liquid propellant rocket engine, similar in its basic parameters to the propulsion system of the MBR 15A18M . TTX missiles : Length - at least 30 m Diameter - about 3 m Starting weight - approx. 200 t Mass thrown - up to 10 t Range - more than 10,000 km KVO - probably less than 200 m Combat equipment : - 14-20 MIRVs in various combinations - estimated data Status : USSR / Russia - preliminary design developed, no further work was carried out.
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