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The main purpose of the "Relief" missile system is to solve operational and strategic tasks to defeat continental targets at known coordinates in advance. He ensured the fulfillment of the assigned tasks in any conditions, day and night, without restrictions on the location during the implementation of the volley.
The development of a new ground-based complex was carried out in pursuit of the American analogue of the Gryphon rocket launcher with the Tomahawk missile. According to the task, the work on the creation of the Relief RC was required to be completed in two years.
The development and design of RK with sea-based (S-10 "Granat") and air-based (X-55, adoption for service -1982) CRBD begins at the end of 1976. Unofficially, the development of a ground modification begins in 1983. Officially, the Republic of Kazakhstan "Relief" is being developed according to the decision of the Council of Ministers and the Central Committee of the party dated 04.10.1984 No. 108-32. The development of the marine RK "Granat" and the KRBD 3M10 developed for it were taken as a basis. The complex receives the name "Relief" and develops the KRBD KS-122 for it. The development was entrusted to the Sverdlovsk design bureau "Novator", the leadership was carried out by the deputy GK A. Usoltsev, and the design team of the GK L. Lyulyev was in charge. Deputy Minister M. Ilyin is appointed responsible for the creation of a new complex from the ministry.
The creation of a launcher, transportation / loading and control vehicles, a ground set of equipment was entrusted to the Sverdlovsk enterprise "Start". The equipment for pre-launch preparation, systems for processing and entering calculated data with on-board equipment of the rocket were created at the Moscow NII-25.
The first prototypes of machines used in the Relief RK were built at the Start enterprise in a very short time - in 1984 they began to undergo sea trials. All tests of the complex were carried out at the Akhtuba training ground of the USSR Ministry of Defense No. 929. In total, during the testing period in 1983 to 1986, 4 rocket mock-ups and 6 complete combat missiles were launched. State tests began in 1985, they took place at the same training ground.
The head of the state acceptance department of the Relief RK was the then commander in chief Soviet Air Force A. Efimov. In 1986, the complex successfully passed the stage of state tests and was put into service. Mass production was carried out at the Sverdlovsk Machine-Building Plant named after Kalinin, where all the necessary documentation for the Relief RK was transferred.
The fate of the complex
The plant managed to produce only one batch of the new RK-55 "Relief" with the KS-122 missile when the Soviet Union and the United States signed the INF Treaty in 1988. The complex was given under the implementation of this Agreement. Specialists were sent from the United States and the entire recently released batch was disposed of at an air base near the city of Jelgava. The beginning of recycling - September 1988, 4 units of KRBD KS-122 were immediately destroyed. Last works destruction were carried out in October 1988. The rocket was the last to be destroyed, on which measurements of the total weight were carried out (used to be pumped into the tanks of conventional diesel fuel) at the request of the Americans.
Device RK-55
The complex consisted of:
- autonomous SPU;
- vehicles for transportation and loading;
MBU control machines;
- ground equipment complex.
The launcher was created on the basis of the MAZ-79111 / 543M chassis as an autonomous self-propelled launcher with the index 9V2413 for 6 CRBD. The composition of the equipment installed on the launcher: equipment for navigation, orientation and topographic reference, automatic production of the rocket launch and equipment for entering flight data. The positional area of work is five thousand kilometers. In the course of the work, it turns out that the usual placement of six missiles will carry a danger in the form of an overload of the chassis, which will lead to a decrease in mobility and missile launch characteristics. Therefore, a decision is made to make missiles with a swinging part of the launcher in a single block. A special launch control system is being developed. The electrical connection connector was made in the back of a single unit.
Key features of the launcher:
- length - 12.8 meters;
- width - 3 meters;
- height - 3.8 meters;
- calculation - the commander of the car and the driver-mechanic;
- power - diesel type D12AN-650;
- diesel power - 650 hp;
- wheel formula - 8X8;
- Weight not equipped / equipped launcher - 29.1 / 56 tons;
- speed up to 65 km / h;
- march range up to 850 kilometers;
- transfer time combat / marching position up to 15 minutes;
- rocket launch time - about a minute;
- missile launch - single / salvo with an interval of about a second.
- overcome obstacles: slope up to 40 degrees, moat up to 3.2 meters;
KRBD KS-122 was created according to the normal aerodynamic scheme with a folding wing and an in-fuselage engine installation. The elevators and rudders are also of a folding type, all-moving. The installed guidance and control system is fully autonomous inertial execution with correction according to the relief data of the correlation extreme correction system, which includes: an on-board computer, a digital data storage system for correction area matrix maps and flight data, a radio altimeter. The onboard guidance system and the rest of the onboard equipment were created by the Moscow Research Institute of Instrument Engineering. It has a block design, in separate cases.
propulsion system intra-fuselage design was developed at the Omsk Engine Design Bureau and at the Soyuz production association. First, Omsk designers developed a small-sized mid-fuselage turbofan engine. The latest development was called 36-01 / TRDD-50. He developed a thrust of 450 kilograms. The work has been carried out since 1976. Tests in 1980 for the Raduga complex were considered successful. Somewhat later, successful tests were also carried out for the Relief complex. However, for the KS-122 rocket, the R-95-300 engine developed by MNPO Soyuz was chosen. The engine developed a thrust of 400 kilograms and was produced at a plant in Zaporozhye.
The main characteristics of the rocket:
- total length - 8.09 meters;
- container length - 8.39 meters;
- wing - 3.3 meters;
- rocket diameter - 51 centimeters;
- container diameter - 65 centimeters;
- starting weight - 1.7 tons;
- weight in TPK - 2.4 tons;
- the weight of the warhead did not exceed 200 kilograms;
- warhead power - 20 kilotons;
- maximum range in the region of 2600-2900 kilometers;
- average flight speed - Mach 0.8;
- average flight height - 200 meters;
- used fuel - kerosene / decilin;
- starting engine - powder solid propellant rocket engine.
Data on RK-55 "Relief"
In 1988, 6 autonomous SPU units were produced with 80 KS-122 CRBD ammunition. All of them were in trial use near the city of Jelgava, Latvian SSR. At the end of 1988, the disposal of missiles was carried out at the same airbase. Most likely, a little more missiles were produced, however, according to available data, only missiles of the experimental complex were received for disposal. It's about about 80-84 KRBD KS-122.
Brief information on the American analogue of the Gryphon complex
The missile of the Gryphon complex called BGM-109G was a ground-based modification of the Tomahawk and had the following data:
- length 6.4 meters;
- weight - one ton;
- average speed 0.7 Mach;
- engine with a thrust of 270 kilograms;
The first rocket launch recognized as successful was made in early 1982. And in 1983, the first serial samples began to enter service.
The composition of the complex:
- 4 TPU vehicles based on MAN AG with a wheel arrangement of 8 X 8;
— 16 cruise missiles BGM-109G;
- two control machines.
In total, about 560 cruise missiles were mass-produced to support the American missile system. A little less than 100 missiles remained in the United States, the rest were supposed to arrive for deployment on the territory of European countries.
The capabilities of the rocket compared to the Soviet counterpart were less effective:
- small RCS;
- range up to 2.5 thousand kilometers;
- average flight height 30-40 meters;
- warhead power up to 150 kilotons.
Combined guidance system. The Soviet missile KS-122 here almost did not differ from the American BGM-109. It had an inertial system and a correction along the contours of the terrain created by the TERCOM company. It also includes an onboard computer and a radio altimeter. The data stored in the on-board computer made it possible to determine the location during the flight with increased accuracy, the KVO was about 20-30 meters.
The main purpose was to disable enemy launchers with strategic missiles, military airfields, various bases for basing and accumulation of manpower and equipment, strategic air defense facilities, destruction of large strategic facilities such as power plants, bridges, dams.
In addition to the ground version, they developed a modification of the rocket for the Air Force. In 1980, when studying the results of a competition in which the AGM-86B from Boeing and the AGM-109 (modification of BGM-109) from General Dynamics participated, the military chose a missile from Boeing.
According to the signed Treaty with the Soviet Union, all launch and cruise missiles of the Gryphon complex were disposed of in the United States. The last BGM-109G missile was disposed of on May 31, 1991. The estimated cost of one BGM-109G is just over one million dollars (for 1991). Eight rockets were "disarmed" and sent to museums and expositions.
Sources of information:
http://military.tomsk.ru/blog/index-762.html
http://militaryrussia.ru/blog/topic-601.html
http://www.militaryparitet.com/html/data/ic_news/42/
http://militaryrussia.ru/blog/topic-697.html
http://en.wikipedia.org/wiki/BGM-109G_Ground_Launched_Cruise_Missile
http://www.youtube.com/watch?v=2YQGiNC9abw
As is known, in 1972 the USSR and the USA signed the Interim Agreement on the Limitation of Offensive Strategic Arms (SALT-1 Treaty), covering land-based and sea-based ballistic missiles. On the principle of reciprocity, strategic bombers (which the United States had a multiple advantage in) and long-range cruise missiles (which then only the USSR had) were withdrawn from the treaty.
In the United States, it was also decided to start developing long-range cruise missiles. In connection with the need to withdraw, in accordance with the Treaty, early-built missile carriers from the fleet, it was decided to consider their re-equipment with cruise missiles launched from torpedo tubes. This decision was due to the need to comply with the provisions of the Mutual Control Treaty. The new cruise missile was named "Tomahawk".
Shortly after the appearance of information about the start of work on new-generation cruise missiles in the United States, similar studies were launched in the USSR. At the same time, the corresponding design developments and research work were conducted much earlier, but were not developed due to successes in the development of heavier supersonic cruise missiles. American work on Tomahawk and ALCM made it possible to give the green light to similar domestic products. By the decision of the military-industrial complex, and then by the Government Decree of December 9, 1976, the development of the Granat complex was entrusted to the Sverdlovsk ICD Novator (OKB-4). By the mid 1970s. its designers designed several samples of missiles for air defense and missile defense systems, including the Krug and Buk, as well as missile torpedoes of the Vyuga and Veter complexes.
Flight testing of the rocket began in July 1976 at the Peschanaya Balka training ground with throw tests of KS-122RS models equipped with a full-scale starting engine to test the drop of the capsule. Further tests were carried out on board an experimental S-49 diesel-electric submarine pr.633RV. To test the "Grenade", the S-49 submarine was re-equipped at the Sevastopol Marine Plant. In the period from July 28 to October 30, 1977, four launches were carried out at the Feodosia deep-water test site. In the first two, the initial flight segment was worked out up to the disclosure of aerodynamic surfaces, and in the course of the subsequent ones, the process of starting the sustainer engine was also worked out. By the end of 1977, testing of the functioning of the rocket began on the main cruising section of the flight. The sustainer stage of the missile equipped with an autopilot was dropped over the Black Sea from a Tu-16KSR-2 aircraft to perform a program flight along an arc 90 km long. However, the specified range was not initially reached. On March 28, launches from submarines again began, which revealed the low reliability of the TRDD-50 propulsion engine. Therefore, it was decided to switch to the use of the R-95-300 engine on the rocket. After a number of unsuccessful launches and ongoing improvements in the second half of 1980, the target flight range of 200-220 km was achieved.
Then, over the course of a year and a half, the rocket was brought to standard equipment, after which the stage of state tests in the North began. Tests in the North started as early as 1979 and began with the testing of shipboard equipment, including the fire control system. In the process of testing, the most complex tasks related to the development of the onboard control system and flights to ranges unheard of for ship-based cruise missiles were successfully solved. The first launch from a boat according to the program of the chief designer was carried out on November 30, 1981. State tests began on April 23, 1982 with a launch from a coastal stand, and from July 21 they continued from the K-254 submarine - the lead submarine pr.671RTMK. their final stage was carried out by launches from submarines from April 8 to August 23, 1983, and in April of the following year, the Granat complex was put into service. In 1988, tests of a missile with a PLA pr.971 were also completed.
The commonality of requirements also determined the similarity of a number of technical solutions embodied in Soviet and American cruise missiles. The choice of torpedo size also determined the main tactical and technical indicators of the designed missiles. In the accepted weight and size restrictions, it was impossible to create a high-speed high-altitude rocket. A breakthrough in air defense could only be ensured through stealth: by reducing the effective dispersion surface and flying at extremely low altitude. There were, however, also differences. So, in accordance with the capabilities of the torpedo tubes of domestic submarines, the Granat had a 15% higher flight weight and was 1.7 m longer than the Tomahawk. On the contrary, the TA 533 mm caliber, which is common for most fleets of the world, determined, in combination with the use of a capsule in the underwater section of the trajectory, the same diameter of the midsection of missiles 514 mm.
The cruise missile "Granat" has a cylindrical shape, due to its launch from a TA, a direct carrier wing of small elongation, which is optimal for long-term flight at transonic speeds, and a cruciform tail. The scheme of the cruise missile is made according to the normal aerodynamic configuration with wings deployed after launch and a tunnel air intake. The launch is carried out using a solid-propellant booster mounted behind the TRD nozzle. For the ultimate lightness of the design of the rocket as an aircraft and minimization of force effects on it in the underwater section of the movement, the rocket is enclosed in a stainless steel capsule, which is dropped after leaving the water. In the underwater section, after leaving the torpedo tube and moving away from the boat by 10-20 m, the rocket in the capsule moves due to the operation of the solid propellant engine. After crossing the water surface, the capsule is dropped. The spent solid-propellant engine is separated, the wing consoles and tail are opened, and the turbojet engine is started, providing further flight to the target.
The Granat missile has a range that is almost an order of magnitude greater than the performance of previously created ship-based cruise missiles. This required the development of a highly economical turbojet engine. No less important, this engine had to have extremely small dimensions and weight. According to the test results, the R-95-300, developed at the Favorsky Design Bureau, was used. In combination with the minimum flight altitude, this also led to the use of an inertial guidance system with radio correction. The tasks of creating small-sized on-board equipment, especially the correction system, were distinguished by novelty and complexity.
The missile system is in service with the PLA pr.671RTMK, pr.971, pr.945A, was in service with the APKRRK pr.667AT. With regard to the last submarine in our country, the "American dream" came true - the plan of rearmament of carriers that was never implemented in the United States ballistic missiles on new generation cruise missiles. And the main carriers of the complex are the most advanced multi-purpose domestic submarines pr.971.
In the strategic arms system Soviet Union complex "Granat", of course, did not have much great importance, which is due to its range of 3000 km. But, nevertheless, its use made it possible to supplement the strike of ballistic missiles with cruise missiles launched from multi-purpose submarines. And this could be decisive. In addition, the appearance of this complex allowed multi-purpose submarines to strike along the coast also when solving operational-level tasks, and when equipping cruise missiles with a conventional warhead, they could use the complex in a non-nuclear conflict. Thus, the Granat complex fits well into the weapons system of our Navy and is a good and high-quality weapon - a complex of the 21st century.
No, this is not about a book with A. Pokrovsky's army stories. We are talking about Russian cruise missiles (hereinafter - KR). After launch 26 pcs. 3M14 on IG talk a lot about them. But at the same time - and a lot of confusion. Let's try to clarify this confusion. :)
By the way, why are cruise missiles good and why are they needed?
CRs have their pros and cons.
The main disadvantages are low speed and long flight duration, as well as vulnerability to even the most simple means Air defense (for example - MANPADS and MZA).
There are more pluses. In favor of the KR they say:
1) their relative simplicity and cheapness,
2) smaller (in comparison with ballistic missiles) dimensions and weight - and, as a result, the possibility of placing missiles on various vehicles,
3) high probability of overcoming enemy air defense due to low flight altitude and "shelter" in terrain folds, and low radar visibility (both due to the low approach height to the target, and due to low EPR).
So what do we have?
1. At sea.
3M10, "Pomegranate"
The 3M10 missile (aka KS-122) was developed at the Novator Design Bureau (now the Novator Design Bureau) and put into service in 1984.
It was developed in response to the American Tomahawks and was intended to be launched from submarines from under water.
Nuclear submarine K-254 pr.671RTM with an additional torpedo tube (before wheelhouse) for testing KR 3M10
Project 971 nuclear submarine
It is used as part of the 3K10 complex, or S-10 "Granat" (according to NATO classification: SS-N-21 Sampson).
The launcher for the CR capsule is a conventional 533-mm torpedo tube (TA).
Flight range: 3000 km.
Warhead: nuclear, 100-200 kt.
3M14, "Caliber"
3M14 is a reincarnation of the good old 3M10, developed by the same Novator Design Bureau.
Created for the Caliber missile system (the export version is known under the name Club). Adopted in 2012.
The launcher for 3M14 is the UKSK vertical mine (universal ship firing system).
Flight range: 2600 km (according to the commander of the Caspian Flotilla, Rear Admiral S. Alekminsky)
Warhead: presumably 450 kg (similar to the export 3M14E).
Our 3M14 looks the same, only 2 meters longer.
Mentally lengthen the hull of the export 3M-14E to the length of the anti-ship 3M-54E (in the figure below) - and you will get our 3M14.
I have only one question - is it possible her shoot from submarine torpedo tubes?
Again, relying on the export 3M-14E (announced for all versions of "Club" and -S / -N / -K), I would venture to suggest that it can.
For more details about the 3M10 and 3M14 missiles, you can look at the logical reasoning of the comrade navy_ship
.
Navy-korabel disagrees with comrade only in justifying the fall in the range of the rocket here:
Particularly on the points 3)
and 4)
.
3)
the lack of expediency to have the same range as that of the "Grenade", from the point of view geographical location potential targets;
4)
the lack of expediency (for example, due to obsolescence of data) of the missile being in flight to the target for more than three hours (corresponding to a range of 2600 km and a speed of 0.7 M).
In my opinion, than farther we can launch a "gift" - those better. As the saying goes "extra kilometers - never superfluous." :)
Actually, my idea is confirmed by the appearance of the X-101/102 CRBD with a range of 5500 km. But let's not get ahead of ourselves - more on that below.
2. On the ground
KS-122, "Relief"
The land version of the "innovative" KS-122 missile for the 3K12 complex (better known as the RK-55 and 9A2413 "Relief") was named 9B2413.
The complex was developed as a response to the American GLCM (Ground-Launched Cruise Missile) complex with the ground version of the Tomahawk BGM-109G. Adopted in 1986.
A variant of the self-propelled launcher of the RK-55 "Relief" complex
The 9V2413 launcher based on the MAZ-543M was supposed to carry 6 TPKs with missiles.
All manufactured complexes were destroyed at the end of 1988. under the INF Treaty.
Range of flight :
3000 km.
Warhead :
nuclear, 100-200 kt.
R-500, "Iskander-K"
KR 9M728(aka R-500) of the Iskander-K missile system, contrary to common misconception not "Innovatorskaya" at all, but "Kolomenskaya" - from the Kolomna Bureau of Mechanical Engineering (KBM). Adopted in 2009. The only CD from the entire list that does not fall under the definition of "strategic".
The launcher based on the MZKT-7930 carries at least 4 transport and launch containers (TLCs) with missiles.
Flight range: 500 km (according to the Ministry of Defense of the Russian Federation -).
Warhead: presumably - at least 450 kg.
It seems to me that the Iskander-K TPK, in addition to the Kolomna R-500, should also include missiles of the 3M14 family.
To be continued:
Complex 3K-10 / S-10 "Granat", missileKS-122 /3M-10 - SS-N-21 SAMPSON
Sea-launched long-range cruise missile. The full-fledged development of a sea-based complex with the KS-122 missile in response to the creation in the United States of the SLCM and GLCM cruise missiles was started by the Novator Design Bureau (Sverdlovsk) by decision of the military-industrial complex under the USSR Council of Ministers No. 282 dated June 19, 1975. The chief designer is L. V. Lyulyev. According to unconfirmed official memoirs ( ist. - Shirokorad) preliminary study of the project of a long-range subsonic cruise missile was carried out at the Novator Design Bureau on an initiative basis in the late 1960s and early 1970s. There is also a legend about one of the test samples of the KR SLCM, which accidentally ended up in Cuba, got into the Novator Design Bureau.
As a result of the research work "Echo" carried out by GosNIIAS in the late 1960s, it was established that it is possible to overcome the enemy's air defense and missile defense system with subsonic cruise missiles in their massive use, as well as using the "counter detonation" technique to destroy enemy air defense and missile defense systems with nuclear explosions from the purpose of clearing the corridor for other attacking CDs. The development of a torpedo-missile system with the KS-122 missile was started by the Design Bureau "Malakhit" ( chief designer- L.A. Podvyaznikov) by order of the Minsudprom dated December 9, 1975 Torpedo- missile system was intended to solve operational-strategic tasks in the continental theater of operations by defeating administrative-political and large military-industrial centers with coordinates known in advance. The complex provided combat use at any time of the day and year, in any weather conditions, in mountainous and difficult terrain.
The official design of complexes with long-range air and sea-launched cruise missiles began in the USSR according to the Decree of the Council of Ministers of the USSR of December 9, 1976. Later, on the basis of the S-10 "Granat" complex with the KS-122 missile, its ground-based version was created -. On May 26, 1978, the Decree of the Council of Ministers of the USSR ordered the processing of the PLA project to accommodate the Granat CRBD.
Missile testing KS-122 was launched in July 1976 in the Crimea by the joint efforts of two ranges - the "Peschanaya Balka" range of the Navy's URAV and the USSR Navy's deep-sea range of the USSR Navy. The technical base for preparing equipment for testing was located at the Deep-Water test site, ground test launches were conducted at the Sandy Balka test site, launches from submarines were tracked by means of both test sites. Processing of test materials was carried out at the "Sandy Balka" test site.
The first launch from a ground-based range launcher during flight design tests at the 21st sea range of the USSR Navy in Nenoksa. 05/25/1981 or 04/23/1982. The starting pencil case-capsule is thrown off, the starting rocket solid propellant rocket engine is working (frames from the film "State Central Sea Range. 50 years.", 2004).
- the first stage of testing: "Experimental testing of the KS-122RS product from the coastal mobile launcher KS-93V3 installed on the T-70 tank." Conducted two launches.
- the second stage of testing - "Experimental tests of the KS-122RT product from a submarine" - the experimental submarine S-49 pr.633RV of the 475th submarine division was used (commander - captain 2nd rank N.N. Sinichkin).
- the third stage of testing - "Testing of products KS-122RP by launches from the Tu-16KSR-2 aircraft to check the aerodynamic characteristics." The launches were carried out from the Tu-16KSR-2 aircraft of the Baltic Fleet Aviation, temporarily based at the Gvardeyskoye airfield between Simferopol and Dzhankoy.
- the fourth stage of testing - "Flight design tests of 3M-10 missiles in various modifications of the manufacture of onboard control equipment." Tested missiles with options for on-board equipment AB-12, AB-13 and AB-51. Starting from December 26, 1978, rockets with the R-95A-300 engine were tested. On May 30, 1980, the first launch was made from the experimental submarine S-128 pr.633KS (the commander is the same - captain 2nd rank N.N. Sinichkin). Submarine pr.633RV no longer participated in the tests of KS-122 missiles. Tests of the fourth stage were carried out at the "Peschanaya Balka" test site and in the Black Sea in the area of Feodosiya (up to and including the 23rd launch).
Joint tests of the S-10 "Granat" complex were carried out at the 21st naval training ground of the USSR Navy in Nenoksa. Flight design tests according to the program of the chief designer, as well as State tests of the complex, were supposed to be carried out on the PLA pr.671RTM K-254 (B-254 from 06/03/1992). In October 1979, the submarine with the premises prepared for the installation of the equipment of the complex arrived by the White Sea-Baltic Canal from Leningrad to Severodvinsk to the delivery base "Dubrava". In the summer of 1980, in Severodvinsk, the main installation work was carried out on the boat to install the equipment of the complex. In the summer of 1981, the installation of the equipment of the complex was completed. In July 1981, complex tests of the equipment of the complex and ship systems with the 3M-10V2 missile were carried out. The act of readiness of the K-264 submarine for the first launch of the KR 3M-102 was signed on 07/29/1981.
Storyboard of the first launch from a ground launcher for flight design tests at the 21st sea range of the USSR Navy in Nenoksa. 05/25/1981 or 04/23/1982 The rocket launches in a capsule-pencil case, which is discarded after the end of the first stage of operation of the starting engine (frames from the film "State Central Sea Range. 50 years.", 2004).
http://www.shipmodels.info).
Submarine K-254 pr.671RTM with an additional torpedo tube for testing KRBD 3M-10 "Granat" (http://www.atrinaflot.narod.ru).
Flight design tests were carried out in the White and Barents Seas from April 23, 1982 to April 15, 1983. State tests began with a launch from the K-254 submarine on July 21, 1982. From August to December 1982, for technical reasons, launches on the State Testing program was repeatedly postponed. After being relocated to Severomorsk in January-March 1983, adjustment work and docking tests of the complex equipment and missiles were carried out on the submarine. On March 30, 1983, an act was signed on readiness for the launch of the 3M-10V5 rocket - the final stage of the State Testing program. April 8, 1983 - the first launch of the 3M-10V5 rocket at the final stage of the State Tests. State tests were completed in the Barents Sea on the K-264 submarine with successful launches on August 23, 1983.
Storyboard of one of the launches from the K-254 submarine pr.671RTM during flight design tests at the 21st sea range of the USSR Navy in Nenoksa, 1981-1983. The rocket starts in a capsule-case, which is thrown off after the end of the first stage of operation of the starting engine (frames from the film "State Central Sea Range. 50 years.", 2004).
The first launches of the KRBD 3M-10 "Granat" with the head PLA pr.971 K-284 were carried out in January 1987 on pacific ocean. Armament tests were completed only in 1988.
Chronology of test launches KR 3M-10 / KS-122 (in progress):
| No. pp | the date | Rocket | Launcher | Launch range | Notes |
| 1 | 05.08.1976 | KS-122RS without control system and propulsion engine | KS-93V-3 | 3.6 km | First stage. Practice dropping a capsule from a rocket. Capsule without head fairing (pipe). The launch was made at an angle of 50 degrees. |
| 2 | 12.08.1976 | KS-122RS without control system and propulsion engine | KS-93V-3 | 3.6 km | First stage. Practice dropping a capsule from a rocket. The capsule is full-time with a head fairing. The launch was made at an angle of 50 degrees. |
| 3 | 28.07.1977 | KS-122RT, AB-12 control equipment, without propulsion engine | Submarine S-49 project 633RV | Second phase. Successful launch from a depth of 40 m - the rocket passed the underwater section in the capsule, left the water, "dropped" the capsule, the wings and the stabilizer opened, the solid propellant rocket engine fired back. | |
| 4 | 10.08.1977 | KS-122RT, control equipment, without propulsion engine | Submarine S-49 project 633RV | Second phase. Successful launch from a depth of 40 m. | |
| 5 | 27.09.1977 | Submarine S-49 project 633RV | 2129 m | Second phase. The first start with the inclusion of the turbofan engine. The launch from a depth of 40 m was normal (the time of movement under water was 4.88 s). The flight lasted 39.5 s, deviation from the headmistress to the left. |
|
| 6 | 20.10.1977 | KS-122RT, control equipment, mid-flight turbofan engine-50 | Submarine S-49 project 633RV | Second phase. The launch from a depth of 40 m was normal. The marching engine turned on. |
|
| 7 | 01.11.1977 | KS-122RT, control equipment, mid-flight turbofan engine-50 | KS-93V-3 | The launch was made at an angle of 50 degrees. | |
| 8 | 24.12.1977 | Tu-16KSR-2 | 57 km | Third stage. The launch from an aircraft without a capsule, the launch was successful at an altitude of 2150 m. On the 35th second of the flight, the rocket reached a given flight level of 1000 m and was supposed to fly in a circle with a radius of 100 km. Due to a malfunction of the turbofan engine-50, the rocket fell into the sea. | |
| 9 | 27.01.1978 | KS-122RP, with control system and sustainer turbofan engine-50 | Tu-16KSR-2 | 82.5 km | Third stage. The launch from an aircraft without a capsule, the launch was successful at an altitude of 2250 m. The rocket flew in a circle with the execution of maneuvers according to the program (5 in pitch, 2 in roll and 3 in course). Flight duration - 376 s, planned range - 90 km. |
| 10 | 28.03.1978 | KS-122RT, control equipment, mid-flight turbofan engine-50 | apparently submarine S-49 pr.633RV | ||
| 11 | 28.03.1978 | KS-122RT, control equipment, mid-flight turbofan engine-50 | apparently submarine S-49 pr.633RV | Fourth stage. Launch for the purpose of finalizing the turbofan engine-50 | |
| 12 | 04.07.1978 | Submarine S-49 project 633RV | 130 km | Fourth stage. Completely successful launch from a depth of 40 m, boat speed 5.1 knots. The planned launch range has been reached. |
|
| 13 | 10.08.1978 | 3M-10V1A, control equipment AB-12 | Submarine S-49 project 633RV | 27.6 km | Fourth stage. The launch from a depth of 40 m was normal. Due to the separation of the turbine blade of the rotor, the TRDD-50 engine turned off. |
| 14 | 26.12.1978 | 3M-10V1, control equipment AB-13 | KS-93V-3 | 24.7 km | The launch was made at an angle of 70 degrees. The first launch of a rocket with the R-95A-300 engine. The planned flight range is 120 km. Due to the failure of the control system, the missile fell at a distance of 24.7 km. |
| 15 | 23.04.1979 | KS-93V-3 | The launch was made at an angle of 70 degrees. Rocket with R-95A-300 engine. The planned flight range is 120 km. Due to the failure of the control system, the rocket fell 8.8 s after launch. | ||
| 16 | 05.06.1979 | 3M-10V1, control equipment | KS-93V-3 | 125 km | Successful launch. The planned launch range is 120 km. Flight time - 506 s, average speed on the march - 240 m / s |
| 17 | 19.07.1979 | 3M-10V1, control equipment AB-51 | KS-93V-3 | 0.9 km | Due to the failure of the control system, the rocket fell 921 m from the launcher. |
| 18 | 23.09.1979 | 3M-10V1, control equipment AB-51 | Submarine S-49 project 633RV | 1.49 km | Due to the failure of the control system, the rocket fell 1490 m from the launch site. |
| 19 | 30.05.1980 | 3M-10, control equipment | Submarine S-128 project 633KS | 23.1 km | Launch from submarine pr.633KS. Due to the failure of the fuel supply system, the engine stopped, the rocket flew 141.7 s, the range was 23.1 km. The planned range is 125 km. |
| 20 | 31.07.1980 | 3M-10, control equipment | Submarine S-128 project 633KS | 21 km | Due to the surge of the R-95A-300 engine, at the 144th second of the flight, the rocket fell. The planned range is 125 km. |
| 21 | 18.09.1980 | 3M-10, control equipment | Submarine S-128 project 633KS | 206 km | Successful launch from a depth of 40 m, sea waves 2-3 points. flight time 1103 s. |
| 22 | 04.11.1980 | 3M-10, control equipment | Submarine S-128 project 633KS | 220 km | Successful launch from a depth of 40 m, sea state 4 points. flight time 1119 s. |
| 23 | 23.12.1980 | 3M-10, control equipment | Submarine S-128 project 633KS | The launch was made from a depth of 40 m with a sea sun of 4 points. When leaving the water, the rocket lost stability and fell at the 20th second of flight. | |
| 24 | 25.05.1981 23.04.1982 | 3M-10V2 | ground polygon launcher | LKI program. | |
| 25 | 30.11.1981 (sources on PLA K-254) 30.12.1981 (film 21 GTSMP) | 3M-10V2 | PLA K-264 pr.671RTM | LKI program. First launch from standard carrier. |
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| 26 | 21.07.1982 | 3M-10V2 | PLA K-264 pr.671RTM | First launch of the State Testing Program. | |
| 27 | 08.04.1983 | 3M-10V5 | PLA K-264 pr.671RTM | The final stage of State tests, the first launch. Barents Sea. |
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| 28 | 15.04.1983 | 3M-10V5 | PLA K-264 pr.671RTM | The final stage of State tests, the second launch. Barents Sea. | |
| .. | 23.08.1983 | 3M-10V5? | PLA K-264 pr.671RTM | The final launches are the launch of the State Testing Program. Barents Sea (according to other sources - the White Sea, Severodvinsk). |
Missile system S-10 "Granat" adopted December 31, 1983 (in April 1984 according to other data and in 1985 according to the data of the Nenoksa test site). By the end of 1988, according to Western data, about 100 3M-10 Granat missiles were deployed on submarines of the USSR Navy. To ensure the combat use of missiles equipped with an extreme correlation guidance system, a special computer center was created in the Navy for the formation of digital maps of the area of proposed theaters of military operations and the development of flight missions.
As of 2012, the S-10 "Granat" complex is probably in service with the Russian Navy, but cruise missiles are not placed on submarines, but are located in the Fleet's bases in storage.
Launcher:
- KS-93V3 - an experimental mobile polygon launcher on the chassis of the T-70 tank - was used at the first stage of testing the CD at the Peschanaya Balka training ground in the Crimea.
533-mm submarine torpedo tubes - missile and torpedo complex developed by Design Bureau "Malakhit" (chief designer - L.A. Podvyaznikov). Development started by order of the Ministry of Shipbuilding Industry dated December 9, 1975 to be placed on submarines pr.671, 671RT, 671RTM, 667A, 670 and 670M. Shipborne fire control system (KSUS) "Acacia" (PLA pr.671RTM at least).
Rocket KS-122RS:
Design- a normal aerodynamic configuration with wings that open after launch and an engine located inside the fuselage. The wings each folded into their own niche in the fuel tank in the rocket body back along the flight. Unlike similar KRBDs of the X-55 type developed by the Raduga Design Bureau, the main engine of the KS-122 missiles did NOT extend from the fuselage after launch. The rudders and elevators are all-moving folding.
Lateral projection of the KS-122 cruise missile of the S-10 "Granat" complex - SS-N-21 SAMPSON (http://forum.keypublishing.com, processed).
An analogue of the 3M-10 "Granat" rocket is the 3M-54E rocket (frame from the film "State Central Sea Range. 50 years.", 2004).
Underwater launch from a torpedo tube on the starting solid propellant rocket engine. Before leaving the water, the rocket is in a capsule-case. After exiting the water, the head fairing of the capsule was cut off from the capsule using a special charge (action time 0.001-0.003 s) and the rocket was released from the capsule under the influence of gases from the starting solid propellant rocket motor.
Control system and guidance- autonomous inertial with correction from the relief-metric correlation-extremal correction system. The correction system includes an on-board computer, a radio altimeter, a system for storing digital matrix maps of correction areas and a flight task. The work of Academician Krasovsky is based on the principles of the correction system. Development of onboard equipment of the guidance system and complex technical means the preparation of flight tasks was conducted by the Research Institute of Instrument Engineering (Moscow, director - A.S. Abramov). Blocks different systems The avionics are made in their own cases, electrical cables, as a rule, are made not "multi-tailed".
Prior to installation on missiles, the onboard equipment of the guidance system was tested on the An-30 aircraft-flying laboratory. During the tests, different versions of on-board equipment were installed on the missiles - AB-12, AB-13, AB-51 and, possibly, others. AB - "on-board equipment".
Shipborne fire control system (KSUS) "Acacia" (PLA pr.671RTM at least).
Engines:
Starting engine (unit) - solid propellant rocket motor weighing 382 kg
Marching - small-sized turbofan engines - on a competitive basis, on the instructions of the MAP for the KRBD KS-122RS, small-sized marching turbofan engines were created with placement in the fuselage in the Omsk Engine Design Bureau and in the MNPO Soyuz.
Omsk engine-building design bureau, chief designer V.S. The design of the turbofan engine began in 1976. State tests of the retractable pylon version of the turbofan engine-50 (for the CRBD MK "Rainbow", product 36) were successfully carried out in 1980, a little later the built-in engine layout was also successfully tested (product 36-01) . After positive state tests and preparations for launching in a series at the Rybinsk Engine Plant (now NPO Saturn), for non-technical reasons, the MAP of the USSR made a choice in favor of the R-95A-300 turbofan engine. Although several unsuccessful test launches due to the fault of the engine, including the launch on 08/10/1978, could play a certain role in making such a decision.
The length of the turbofan engine - 850 mm
Diameter - 330 mm
Dry weight - 82 kg
Fuel grades - T-1 (aviation kerosene), T-6, T-10 (decillin), TS-1, RT
Oil - VT-301
Specific fuel consumption at maximum mode - 0.71 kg / kgf per hour
A later version of the unmanned (built-in) turbofan engine "product 37-01E" developed and produced by OMKB (http://www.uk-odk.ru).
A variant of the engine for the KR ICB "Rainbow" with a pylon installation - a small-sized engine TRDD-50AT ("product 36MT") developed and produced by OMKB, MAKS-2005 exhibition (photo - Evgeny Erokhin, http://www.missiles.ru).
- MNPO "Soyuz", chief designer - O.N. Favorsky - R-95A-300 turbofan engine / item 95 / R-95TM-300 with a thrust of 400 kg. Production was mastered at the Zaporizhzhya Machine-Building Plant (Ukraine).
Length - 850 mm
Diameter - 315 mm
Dry weight - 100 kg
Fuel - T-1 (aviation kerosene), TS-1, T-10 (decilin)
TTX missiles:
The length of the rocket with a starting solid propellant rocket engine - 8090 mm
Marching rocket length - 6200 mm
Wingspan - 3300 mm
Rocket fuselage diameter - 510 mm
Capsule diameter:
- internal - 518 mm
- outer - 533 mm
Launch weight in capsule - 2385 kg (KS-122RT, launch 09/27/1977)
Starting weight:
- 1485 kg (KS-122RT, launch 09/27/1977)
- OK. 1700 kg (3M-10)
Weight without starting engine - 1103 kg (KS-122RT, launch 09/27/1977)
Weight starting solid propellant rocket engine - 382 kg
Warhead weight - up to 200 kg
Range - 3000 km (maximum, data not confirmed)
cruising speed:
- 240 m/s (tests, 1979)
- 720 km/h
- 0.7 M
Ceiling cruising - 15-200 m
Launch depth - 40 m (during testing)
The time of passage of the underwater section after launch is 4.88 s (KS-122RT, launch 09/27/1977)
Warhead types:
- nuclear, with a capacity of 200 kt - the main type of warhead.
High-explosive - according to Western data, it was developed and possibly installed on missiles placed on boats (unlikely).
Modifications:
- KS-122RS - the first experimental version of the KS-122 rocket, apparently "Static" - without a control system and a main engine.
KS-122RT - the second experimental version of the KS-122 missile, apparently "Telemetric" - with an inertial control system (autopilot) and a main engine. The missiles performed a straight flight.
KS-122RP - the third prototype of the KS-122 missile, apparently "Program" - was intended for test launches from the Tu-16KSR-2 aircraft with an inertial control system (autopilot) flight with program maneuvers.
3M-10V1A - version of the missile for testing with the TRDD-50 engine and AB-12 control equipment, launched in 1978.
3M-10V1 - a version of the rocket with the R-95A-300 engine and various control equipment options, first launch on 12/26/1978.
3M-10V2 - a version of the rocket with the R-95A-300 engine for flight design tests from submarines. The first launch from a ground stand - 04/23/1982
3M-10V5 - a variant of the rocket used at the final stage of State tests, first launch - April 8, 1983
KS-122/3M-10 is the basic variant of a sea-launched long-range cruise missile.
Sources:
Asanin V. Rockets domestic fleet. ().
"State Central Sea Range. 50 years". Documentary, 2004
. 2012
Shirokorad A.B. Fire sword Russian fleet. M., Yauza, Eksmo, 2004
Depth Storm. Website
S-10 "Granat" is a sea and land-based missile system with a subsonic small-sized long-range cruise missile.
In the early 1970s, progress made in the creation of small-sized economical turbojet engines allowed work to begin on relatively small long-range cruise missiles. In the United States, work began on a number of missiles, including a unified family of land-based and sea-based SLCM / GLCM cruise missiles (and sea missiles could be launched both from surface ships and submarines), which later, after being put into service, became known like Tomahawks.
In the USSR, similar solutions were worked out. Since 1975, the Novator Design Bureau officially began work on marine complex for use in submarines. The cruise missile received the internal index KB KS-122. First launch from ground test launchers a full-fledged rocket took place in 1981. In 1983, the missile passed state tests and was put into service as part of the arsenal of nuclear submarines of projects 667AT "Grusha"; 671RTM (K) "Pike"; " " .
Cigar-like rockets did not have high speed flight, but bribed with a very interesting ratio of range (2000-3000 km) and the ability to place them on carriers that were not previously used for strategic weapons. Overcoming air defense was provided due to reduced radio visibility and flight at low and ultra-low altitudes in radio silence. Like the Tomahawks, the Grenades were originally designed to be launched directly from 533mm torpedo tubes. With the entry into service of "Grenades", the number of submarines in the Soviet fleet capable of inflicting practical strategic nuclear strikes, on the scale of a hypothetical European theater of operations, has increased significantly.
In addition to cruise missiles for submarines, in 1983, the Novator Design Bureau was given the task to develop a ground-based mobile missile system with KS-122 missiles as soon as possible. The complex was named RK-55 "Relief". In many ways, it was created as a symmetrical response to the BGM-109G "Gryphon" - the land version of the "Tomahawk". State tests of the RK-55 "Relief" passed in 1985-86, in 1986 the complex was put into service. However, they managed to release only a small experimental batch - in 1987, an American-Soviet agreement was signed on the elimination of medium and short-range missiles. In 1988, all issued RK-55 "Relief" (as well as BGM-109G) were destroyed.
Unlike ground systems with ballistic missiles, complexes with cruise missiles carried several missiles at once: the American Griffon carried four Tomahawks, and the Relief carried six KS-122s at once. Combined with the low visibility of the launch and the higher effectiveness of the missiles over land, where they could hide in the folds of the terrain, this allowed them to be used to strike important targets in Europe after an exchange of ballistic missile strikes.
Complex RK-55 "Relief". Photo: militaryrussia.ru
AT this moment the S-10 "Granat" complex is probably still in service with the Russian Navy, however, in accordance with international agreements, missiles in combat equipment are stored at the bases. It is being replaced by a promising family of Caliber cruise missiles.
Technical solutions, worked out on the RK-55 "Relief", apparently, were used to create the latest soil complex with cruise missiles "".
Main characteristics:
- Firing range - 2500-3000 km (according to various sources),
- starting weight– about 1700 kg,
- Dimensions, m:
- length 8.09 (with starting accelerator),
- diameter 0.51,
— wingspan 3.3, - Rocket flight speed - 720 km / h.,
- Warhead - nuclear, equivalent power - 200 kT.
