Description: War Thunder is a next generation military MMO game dedicated to...
DATA FOR 2017 (standard replenishment)
Complex 9K72 "Elbrus", rocket R-17 / 8K14, SPU 2P19 - SS-1B SCUD-A
Complex 9K72 "Elbrus", rocket R-17 / 8K14 - SS-1C SCUD-B
Complex 9K72 "Elbrus", rocket R-17 / 8K14-1 - SS-1C SCUD-B
Complex 9K72M "Elbrus-M" (?), missile R-17M - SS-1D SCUD-C / KY-03
Complex 9K73, missile R-17V / 8K114 ("helicopter")
Complex 9K72-O, missile R-17VTO / 8K14-1F "Aerofon" (with optical seeker) - SS-1E SCUD-D
R-300 - export designation of the missile complex 9K72
Operational-tactical missile system. The development was carried out in SKB-385 under the leadership of chief designer V.P. Makeev (deputy chief designer - V.R. Serov, lead designer - Yu. 11MU) since 1957. As a result of research work, in December 1957, the SKB came up with a proposal to create an OTR with a doubled range compared to the R-11M by replacing the engine with an engine with a turbopump unit and finalizing the rocket.
On February 24, 1958, documents of the military-industrial complex under the USSR Council of Ministers were signed and the Decree of the USSR Council of Ministers on the creation of an OTR complex based on R-11M No. 378-181 was issued on April 1, 1958. The draft design was defended at NII-88 in September 1958, the release of design documentation completed in November 1958. The production of an experimental series and prototypes (R-17 - option 1 - OKB-3 engine) was carried out at the SKB-385 plant in Zlatoust in 1958-1959. In April 1959, the tactical and technical requirements of the GAU of the USSR Ministry of Defense for a rocket were received. In May 1959, TTT was approved, and the GAU 8K14 rocket index was received. According to the Decree of the Council of Ministers of the USSR of June 17, 1959 No. mass production R-17 / 8K14 missiles (R-17 - option 2 - OKB-5 engine - since 1962) were carried out at the Votkinsk Machine-Building Plant No. 235 (Votkinsk, a series from 1959 to 1985). At the end of July 1959, the assembly of the first two missiles for firing tests began. The assembly of missiles for flight tests began in August 1959.
Rocket 8K14 of the 9K72 complex with SPU 9P117 (photo by V.P. Makeev Design Bureau)
Complex 9K72 SS-1C SCUD-B on SPU 9P117M at the Parade on Red Square in Moscow (May 9, 1985)
Flight tests of the R-17 rocket were carried out at the Kapustin Yar test site from December 12, 1959 to August 25, 1961 (first stage - 7 launches - all successful). The second series of missiles for testing (R-17 - option 2) was produced at the Votkinsk plant from April 1960 (2 bench - readiness in June 1960, flight - July 1960). Fire tests of the second series - July 1960. The second stage of flight tests began at the Kapustin Yar test site on August 25, 1960 (a total of 25 launches were carried out, the first launch was unsuccessful - the rocket flew in the opposite direction, the third launch was also unsuccessful - loss of control on the active site due to a short circuit, the rest are successful). On December 12, 1960, the third stage of testing began. Tests with a wheeled SPU 2P20 were carried out in 1961. Launches at a distance of 300 km were carried out on August 25, 1961 (2 launches, successful). The complex with SPU 2P19 took part in the parade on Red Square in Moscow on November 7, 1961 (4 SPU). The R-17 / 8K14 missile was put into service on March 24, 1962 as part of a complex with a tracked SPU 2P19 (a total of 56 pieces were produced). In 1962, the 3rd Central Research Institute of the USSR Ministry of Defense prepared firing tables for the 9K72 complex with the 8K14 missile.
Decree of the Council of Ministers of the USSR No. 1116 of October 10, 1962 began the development of a new SPU for the R-17 rocket on the MAZ-543 wheeled chassis. In 1964, flight tests of the modernized R-17M missile (8K-14-1, adopted and mass-produced) were carried out. On November 7, 1965, the 9K72 complex with SPU 9P117 was first shown at the Parade on Red Square in Moscow. In 1965, the Pentagon obtained satellite images of a new extended-range R-17 missile ("R-17M"), which was identified as KY-03 (Kapustin Yar).
By Decree of the Council of Ministers of the USSR No. 75-26 of January 27, 1967, the Elbrus 9K72 complex was adopted as part of the R-17 rocket (8K14 and 8K14-1) modernized during the production process and SPU 9P117 on the MAZ-543A (SCUD-B) chassis ). Serial production of SPU 9P117 / 9P117M was carried out at the Petropavlovsk Heavy Machine Building Plant (Petropavlovsk) starting in 1970 (release of the pilot batch - from May 1965) until the end of the 1980s (more than 800 units were produced in total). The export version of the 9K72 complex was called R-300. Later, the design documentation for the rocket was transferred to the Votkinsk Machine-Building Plant.
Launcher:
R-17 / 8K14 - tracked SPU 2P19 / 2P19-1 ("object 810") based on the ISU-152 (IS-2) was developed at the Kirov Plant (Leningrad) under the leadership of K.N. Ilyin. The installation was mass-produced by the Kirov plant. Withdrawn from the USSR Armed Forces with replacement by 9P117 and modifications from 1967 to 1976. It remained in service with two missile brigades until 1989 at least (a missile brigade in the Caucasus and in the village of PinOzero with an ATGM in Kandalaksha).
Crew - 8 people
SPU length - 7.05 m
SPU length with rocket - 12.6 m
Width - 3.24 m
Height on the march - 3.3 m
Ground clearance- 48 cm
Mass of SPU with a rocket - 42.5 t
Engine power (diesel A-308) - 520 hp
Maximum speed on the highway - 40 km / h
Maximum speed on the ground - 25 km / h
Movement speed with a fueled missile with or without warhead:
40 km/h (highway, up to 500 km, according to instructions)
25 km / h (ground, up to 500 km, according to instructions)
40-50 km / h when loading SPU 2P19 onto the MAZ-5247G trailer (ground and highway, respectively, according to the instructions)
Range on the highway - 500 km
Radio stations - R-113 and R-108 (1 each)
SPU 2P19 with R-17 missile and without missile at the Museum of Artillery (St. Petersburg, 2007)
SPU 2P19 with R-17 missile (Equipment and weapons. No. 2 / 1990)
SPU 2P19 with R-17/8K14 SS-1B SCUD-A missile, April 1974. SPU tail numbers - 401 and 410
(Soviet military review. No. 8 / 1985)
Complex 9K72 - rocket - R-17 / 8K14 - experimental wheeled SPU 2P20 on the MAZ-535 chassis. Tests were conducted in 1961-1962. (not exactly). The test did not pass - it was required to strengthen the frame.
R-17 / 8K14 - experimental tracked SPU type 2P19 - "object 816" / "object 817". SPU on the basis of ISU-152 was developed by the Design Bureau of the Kirov Plant under the leadership of K.N. Ilyin, the general designer was Zh.Ya. The "object 817" installation was released as a prototype, the "object 816" installation was released as an experimental batch.
Experimental SPU "object 817" (Kotin Zh.Ya, Popov N.S., Without secrets and secrets. S.-Pb., 1995)
R-17V / 9K73 - light 4-wheeled launcher 9P115 / VPU-01 (helicopter launcher), designed for transportation by Mi-10 or Mi-6RVK helicopters. SPU was developed by GSKB / KBTM under the leadership of L.T. Bykov. The prototype SPU 9P115 was made in 1963. The tests were completed in 1965.
Complex 9K72 - rocket - R-17 / 8K14 / 8K14-1 - SPU 9P117 / 9P117M / 9P117M1 / 9P117M1-1 / 9P117M1-3 on the chassis MAZ-543 "Hurricane". The lead developer for ground systems of the complex is GSKB ( chief designer V.P. Petrov, lead designer S.S. Vanin), aiming devices - design bureau of plant No. 784 of the Kyiv Council of National Economy (chief designer S.P. Parnyakov), for SPU - Central Design Bureau TM (chief designer - N.A. Krivoshein). Serial production of SPU 9P117 / 9P117M and others has been carried out since 1965 at the Barrikady plant, and since 1970 (at least) at the Petropavlovsk heavy engineering plant (Petropavlovsk).
The first version of the layout of the SPU on the MAZ-543 chassis according to the creators documentary film"Cars in uniform" (TRK RF Armed Forces "Zvezda", 2009)
SPU 9P117, you can clearly see the hydraulic lift bars at the rear of the machine, which disappeared on later modifications (photo - Zaloga Steven J., Scud Ballistic Missile and Launch Systems 1955-2005. Osprey Publishing. 2006).
SPU 9P117-1 differs from 9P117 in that the indicator block P61502-1 for the chemical warhead 8F44G / 8F44G1 has been added;
SPU 9P117M (series at least 1968-1976) - differs from 9P117 by changing the boom lifting mechanism to work with larger mass rockets (the hydraulic system has been changed). In addition, SPU 9P117 / 9P117-1 had a device for craneless loading of a rocket onto a rail (on 9P117M and later it was considered inappropriate). Incl. was produced for export without KBU equipment and console equipment for chemical warheads. In 1970, at the Parade on Red Square in Moscow, they were first shown to the public along with SPU 9P117.
Comparison of SPU 9P917 and 9P917M (photo by the US Department of Defense,
Zaloga Steven J., Scud Ballistic Missile and Launch Systems 1955-2005. Osprey Publishing. 2006)
SPU 9P117M-1 - similar to 9P117M, but with indicator block P61502-1 for chemical warhead 8F44G / 8F44G1;
SPU 9P117M1 differs from the previous ones in the use of a new auxiliary power unit (APD-8-P / 28-2M with a radiator from a GAZ-69 car instead of APD-8-P / 28-2 with a radiator from a GAZ-20 Pobeda car).
The engine is a 12-cylinder diesel D12AN-650 with a power of 650 hp.
SPU 9P117M1 of the Polish Army, the picture shows a thermal cover 2Sh2 for warheads (photo - W.Luczak from the book Zaloga Steven J., Scud Ballistic Missile and Launch Systems 1955-2005. Osprey Publishing. 2006)
SPU 9P117M1-1 (series at least 1969-1980) - post 2V12M-1 and 9V362M1 (KBU) installed;
SPU 9P117M1-3 - an automated combat control system was installed (to control the delivery of strikes?).
TTX SPU 9P117M:
The engine is a 12-cylinder diesel D12A-525 with a power of 525 hp. at 2100 rpm with a displacement of 38880 cc
Crew (calculation) - 4 people. (2 cabins for 2 places in tandem)
Wheel formula 8 x 8 with independent suspension, the first two axles are swivel, tires with automatic inflation.
SPU length - 13360 mm
SPU width - 3020 mm
The height of the SPU with a rocket - 3330 mm (stowed position), 13670 mm (combat position)
Base - 7700 mm
Clearance - 440 mm
Track - 2375 mm
SPU weight - 30.6 tons (without rocket and crew), 37.4-39 tons (with rocket and crew)
Movement speed with an unfilled missile without a warhead:
Up to 60 km / h highway (distance up to 2000 km, according to the instructions)
Up to 40 km/h ground (distance up to 500 km, according to the instructions)
The speed of movement with a fueled missile with or without warheads is 60 km / h (highway), 40 km / h (ground) at a distance of up to 2000 km (according to instructions)
Power reserve - 650 km (highway), 500 km (ground)
Minimum turning radius along the track of the outer wheel - 13.5 m
Boom lifting time without a rocket to the starting position - 2.0-3.5 minutes
Time to lift the rocket to the launch position - 2.25-3.5 min
The time for the descent of the boom without a rocket to the pre-launch position is 3.0-4.4 minutes
The time of the descent of the rocket to the pre-launch position - 3.0-4.0 min
Horizontal pointing angles - + -80 degrees.
The SPU was equipped with a R-123 radio station and an R-124 intercom. SPU fit into the railway. dimensions 1B (USSR) and 02-T (Western Europe).
Soil truck 2T3 / 2T3M / 2T3M1:
The speed of movement with an unfilled missile without warheads and in a hermetic seal:
Up to 40 km / h highway (distance up to 2000 km, according to instructions)
Up to 20 km/h ground (distance up to 500 km, according to the instructions)
The speed of movement with an unfilled missile with a warhead is 10 km / h (at a distance of up to 15 km, smoothly, according to the instructions)
The speed of movement with a fueled missile with or without warheads is 40 km / h (highway), 20 km / h (ground) at a distance of up to 2000 km (according to instructions)
Launch pad for 8K14 missiles of the 9K72 complex
Mi-6PRTBV - a mobile rocket-technical helicopter base. Developed in 1960 and tested in 1960-1962. PRTBV is designed for transportation to the launch site of R-11M and R-17 missiles by Mi-6 helicopter.
Rocket R-17 (8K14, 8K14-1) is a ballistic missile with load-bearing fuel tanks and an inseparable warhead. Due to the use of a pumping fuel supply system, the pressure inside the R-17 rocket tanks was reduced by more than 6 times compared to the R-11M, which made it possible to reduce the thickness of the tank walls. The fuel tank is located in front of the oxidizer tank.
Case material - steel 12G2A, stainless steel EI712, aluminum alloys V95, AK-6, AL-4.
The material of the tanks is 1X21H5T alloy (fuel and oxidizer tanks) and/or EI-811 stainless steel (source - "SKB-385...")
Rocket 8K14 / R-17, on the first photo is a rocket with an overall weight model of a warhead (photo by the Design Bureau named after V.P. Makeev)
Rocket 8K14 (R-17 - SCUD-B).
Control system and guidance- the missile control system is inertial, the missile is guided by aiming at the launch pad, on the active part of the trajectory using gas-dynamic rudders (steering gears 1SB14, 4 pcs., graphite rudders 0100-0A / 8A61) the rocket is stabilized on the trajectory. The control system includes a gyroscopic integrator of longitudinal accelerations / automatic range 1SB12 (speed control, and, accordingly, flight range, issuing a command to cut off the engine), a 1SB10 gyro-verticant with a lateral acceleration gyrointegrator and a 1SB9 gyrohorizon (for rocket stabilization), a 1SB15 time mechanism and 1SB13 stabilization automaton calculating and decisive device (continuous operation time up to 2 hours 15 minutes, 1SB13M modification can work 4 hours). In 1967-89. R&D of an optical digital guidance system was carried out (see below). The start can be made from the remote control panel 9V344.
The use of the 9K72 complex can be carried out using the Pled or 1U120 Viscose automated strike control systems with data transmission via R-412 radio relay stations by telecode.
In preparation for the launch, data are taken on the state of the atmosphere up to an altitude of 60,000 m - to make adjustments to the missile guidance depending on the wind - for this, meteorological probes RKZ-1 are used, the behavior of which is monitored by meteorological radars of the RMS-1 (END TRAY), RPS-1 types (BREAD BIN) or ARMS-3 "Smile" (complex 1V44 RPMK-1 LEG DRIVE). Wind data is fed into the 9S436 command vehicle. The weather bulletin is prepared by a meteorological battery (it includes the direction and speed of the wind at standard heights, the temperature in these layers). The meteorological bulletin from the meteorological battery arrives at the headquarters of the missile brigade, from where it is transmitted to the divisions.
The control system of the 8K14 rocket was developed by NII-592 (chief designer - N.A. Semikhatov), gyroscopes - NII-944 (chief designer V.I. Kuznetsov), electroautomatic detonation nuclear charge- NII-1011 (chief designer - S.G. Kocharyants, scientific supervisor - Yu.B. Khariton), aiming devices SPU - Design Bureau of Plant No. 784 of the Kyiv Council of National Economy (chief designer - S.P. Parnyakov). Unlike the R-11M, the instruments of the missile control system are concentrated in a special instrument compartment.
For variants of 8K14 missiles of the 9K72 complex with homing systems - see section Modifications and designations(below).
Gyroverticant 1SB10 of the R-17 missile
(Zaloga Steven J., Scud Ballistic Missile and Launch Systems 1955-2005.
Osprey Publishing. 2006).
The location of the control equipment on the rocket 8K14 (R-17 - SCUD-B).
The location of the control equipment on the split model of the 8K14 / R-17 / SCUD-B missile in the demonstration hall in Orevo (photo - April 2014, http://users.livejournal.com/___lin___/, processed).
Engine:
R-17 (option 1)- single-chamber LRE S3.42T OKB-3 (chief designer - D.D. Sevruk, lead designer - N.I. Leontiev) - was used at the design stage and in the first series of R-17 missiles. The engine was developed on the basis of the C3.42A liquid-propellant rocket engine.
Dry weight - 160 kg
Thrust - 13000 kg (approx)
R-17 (option 2)- single-chamber LRE C5.2 / 9D21 OKB-5 (chief designer - A.M. Isaev, lead designer - N.V. Malysheva), created on the basis of C2.253A of the R-11M rocket. The combustion chamber of the engine and the supercritical part of the nozzle have been redesigned. Open circuit engine with TNA and gas generator. Starting spin-up of the TNA turbine - from a solid fuel launcher, operation in the mode from a gas generator on the main components. The engine was mass-produced from 1962 to 1985 by the Votkinsk Machine-Building Plant. The design support of the LRE was also carried out by the Votkinsk plant, chief designer V.E. Tokhunts.
Fuel - kerosene mixture TM-185 - 56 + 1.5% polymer distillate; 40+1.0% light pyrolysis oil; 4+0.5% tricrysol
Oxidizing agent - AK-27I - 69.8-70.2% nitric acid HNO3; 24-28% nitrogen tetroxide N2O4; 1.3-2% water H2O; 0.03% aluminum oxide Al2O3; inhibitor 0.12-0.16% iodine I2
Starting fuel - TG-02 "Samin" - 50 + 2% triethylamine (with diethylamine); 50+2% isomeric xylidine; up to 0.4% H2O (short for "GIPH-02 fuel", also "Samin") GOST 17147-80
Starting method - self-ignition of starting fuel and oxidizer
Fuel supply - turbopump unit powered by a gas generator
Thrust - 13310-13380 kg (according to various sources)
Specific thrust on the ground - 230 kg per kg / s
Fuel consumption - 57.83 kg / s
Impulse at sea level - 226 sec
Impulse in vacuum - 258 sec
Length - 1490 mm
Maximum diameter - 770 mm
Combustion chamber diameter vnutr.- 380 mm
Nozzle throat diameter - 124.5 mm
Nozzle outlet diameter - 400 mm
Number of nozzles - 519 pcs
Dry weight - 120 kg
Pressure in the combustion chamber - 69.4 kg/sq.cm
Nozzle pressure - 0.827 kg/sq.cm
Engine resource - 100 sec
Engine 9D21 (photo - Zaloga Steven J., Scud Ballistic Missile and
Launch Systems 1955-2005. Osprey Publishing. 2006).
circuit diagram 9D21 engine of the 8K14 SCUD rocket.
Rocket R-17 / 8K14, view from the side of the engine. The graphite gas-dynamic rudders and the gas generator nozzle are clearly visible (http://www.modelwork.pl).
Gas-dynamic rudders of the 9D21 engine of the 8K14 / R-17 rocket in the showroom in Orevo (photo - April 2014, http://users.livejournal.com/___lin___/).
Fuel - kerosene mixture TM-185 (OST V6-02-43-84).
Weight (at temperature):
795 kg (at -40 or +50 degrees C)
822 kg kg (at +20 degrees C)
Polymer distillate - 56+-1.5%
Light pyrolysis oil - 40+-1.0% (to increase density and oxidation resistance)
Trikrizol - 4+-0.5% (prevents water crystallization at negative temperatures)
Oxidizing agent - nitric acid HNO_3 (AK-27I "Melange" GOST B18112-72).
Weight (at temperature):
2825 kg (at -40 degrees C)
2830 kg (at +50 degrees C)
2919 kg (at +20 degrees C)
Concentrated nitric acid - 69.8 - 70.2%
Nitrogen tetroxide - 24 - 28%
Water - 1.3 - 2%
Aluminum salts - no more than 0.01%
Iodine - 0.12 - 0.16% (inhibitor)
Density - 1.596 - 1.613
Starting fuel - TG-02 "Samin" (GOST V17147-71), weight - 30 kg / 35 + -1 liters, is poured into the rocket immediately before launch.
Isomeric xylidines - 50+-2%
Technical triethylamine - 50+-2%
Water - up to 0.4%
Density 0.835-0.855
TTX missiles:
Data for 8K14 - domestic, for SCUDs - Western
| 8K14 | SCUD-B | SCUD-C | SCUD-D | |
| Rocket length | 11250 mm | 11250 mm | 12290 mm | |
| Case diameter | 880-885 mm | 885 mm | 885 mm | 885 mm |
| Stabilizer span | 1810 mm | 1800 mm | 1800 mm | 1800 mm |
| Starting weight | 5840-5950 kg | 5900 kg | 6370 kg | 6500 kg |
| Warhead weight | 987-1016 kg | 550-989 kg | 600-700 kg | 985 kg |
| Empty weight (with warhead) | 2076 kg | |||
| Mass of fuel and air | 3786 kg |
Note. - hull diameter 8K14 according to TTX - 880 mm, but some warheads have a midsection diameter of 884-885 mm.
Starting weight (8K114) - 5860 kg
The mass of the oxidizer - 2919 kg
Fuel weight - 822 kg
Weight of starting fuel - 30 kg
Mass of compressed air - 15 kg
The mass of an empty rocket with warhead 8F14 - 2076 kg
The mass of an empty missile with warhead 8F44 - 2074 kg
The mass of the fueled missile with warhead 8F14 - 5852 kg
The mass of the fueled missile with warhead 8F44 - 5860 kg
Range:
240 km (R-17 / 8K14, according to calculated data, 1957, as well as R-17 option 1)
50-240 km (R-17 / 8K14, according to the Decree of the Council of Ministers of the USSR on the creation, 1958)
270 km (R-17 prototype and first releases?)
50-300 km (R-17 / 8K14 / 8K114, minimum and maximum range)
275 km (R-17/8K14, guaranteed range)
450-575-600 km ("R-17M" SCUD-C, various Western data)
300 km (9К72О SCUD-D)
R-17 prototype and first series - up to 2000 m
9К72О (SCUD-D) - 50 m
Trajectory speed:
1500 m/s (maximum)
1130 m/s (at apogee)
1400 m/s (final stage)
The maximum height of the trajectory is 24-86 km (min.-max. range)
The launch of the 8K14 rocket is allowed at temperatures from -40 to +50 degrees C and wind speeds up to 15 m/s with gusts up to 20 m/s.
Flight time - 165-313 s (50-300 km)
Time of the active part of the flight - 90 s (maximum range), 48 s (minimum range)
Launch time of the SPU 9P117M rocket:
Ready #1 - 5 minutes
From readiness No. 2 - 10 minutes
Ready #3 - 18 minutes
Preparation time for launch according to TTZ at the beginning of R&D - 60 min
Preparation time for launch based on test results - 25 min
Start-up time from readiness No. 1 - 15 minutes (spin-up of gyroscopes, switching on of rocket electrical circuits)
Time to start the starting sequence of commands - 12 seconds before the start
Start preparation time - up to 60 minutes
Temporary standard for loading a rocket from a transport semi-trailer to a SPU - 45 min
Time to stop the rocket gyro instruments before transportation (in case of refusal to launch) - 20 minutes
Time of continuous operation of the onboard equipment of the rocket (before launch) - no more than 2 hours
The maximum shelf life of 8K14 / 8K14-1 missiles in the arsenal is 22 years (can be extended up to 24 years)
The maximum shelf life of 8K14 / 8K14-1 missile gyro instruments in the arsenal is 19.5 years
Warranty period of storage of missiles 8K14 / 8K14-1 - 7 years
The warranty period for storage of 8K14 / 8K14-1 missiles in the field in an unfilled state is 2 years
Warranty period of storage of fueled missiles 8K14 - 1 year
Warranty period of storage of refueled 8K14 missiles in hot climates - 6 months
The warranty period for fueled 8K14 missiles in a vertical position is 7 days
Combat equipment - the missile is equipped with an inseparable warhead (warhead). Through the connectors, the warhead equipment is connected to the missile control system. The warhead equipment interface circuit is designed to check the state of the warhead, check the cocking circuits of the warhead and remove the first stage of protection in flight (the circuit is the same for all warheads). The cocking circuits of warheads are brought into working condition after the rocket is separated from the launch pad. 4 seconds after the 1SB12 device gives the command to turn off the engine, a command is sent to remove the first stage of protection. Through the Sh5A connector, the emergency detonation system of the rocket is connected to the actuating elements of the detonation system in the head part (fuze 8V53), and the circuit for removing the second stage of protection is also being prepared. The second stage of protection is removed during the descent of the rocket from 5000 m to 3000 m. Through connector 03, the cable trunk from the OSHO connector in the tail section of the rocket is connected to the electrical system for internal heating of the warhead in nuclear equipment. The bottom fuse 8V53 of the emergency detonation system destroys the warhead when a signal for an emergency detonation is received from the APR system (lead designer of the APR system - L.N. Maslov, SKB-385). All warheads in nuclear weapons are equipped with internal heating systems with a 2Sh2 thermal cover, which made it possible to remotely control the charge temperature and charge heating. The control equipment of the nuclear warhead allows you to set the type of explosion: ground, low air or high-altitude air. All special warheads (nuclear, chemical) are transported separately and installed on the missile before use.
Warhead types R-17 missiles and variants (8K14 and 8K14-1):
High-explosive concentrated action 8F44 (1959-1962), weight 987 kg (export version - 8F44E). Developed with a detonation system at NII-6. Undermining methods:
Contact head fuse - 8V11706 with contact device 8V11101
Bottom fuse 8V11702 is initiated by the barometric unit 8V11703 (explosion at a height above the ground)
Fuse of the emergency detonation system - 8V53
Explosive - TGAG-5. After the explosion of the warhead, a funnel is formed with a depth of 1.4 to 4 m and a diameter of 12 m. The warhead is stored in container 9101-0A/8F14.
Length - 2650 mm
Midsection diameter - 884 mm
Warhead weight - 987 kg
Damage radius (according to Western data) - 50 m
The main types of warheads of the 8K14 rocket (R-17 - SCUD-B). The previous version of this picture was uncorrect.
Nuclear warhead - building 8F14 warhead"269A" RDS-4 charge (1959-1962) with a capacity of 10 kt. Explosive device of special equipment DU-APR. The warhead was developed by VNIITF (Kasli) / NII-1011 MSM (chief designer - S.G. Kocharyants, scientific supervisor - Yu.B. Khariton).
Warheads are stored in container 9101-0A/8F14.
Length - 2870 mm
Midsection diameter - 884 mm
The center of gravity of the hull of the MS (from the end of the docking frame) - 892 mm
The center of gravity of the fully equipped warhead (from the end of the docking frame) - 787 mm
The angle of the semi-opening of the cone of the bow of the warhead - 9 degrees 35 minutes
Warhead body weight - 278.3 kg
Warhead weight - 989 kg
The maximum temperature inside the warhead case in flight is +50 degrees
During operation, at least 3 days before launch, the warhead temperature is maintained at 20 degrees C (+-5 degrees C) at an air temperature of +15 to -40 degrees C.
During storage, it is allowed to maintain the warhead temperature from +5 to +35 degrees C.
8F14UT - training version of warhead
Chemical 3N8 (1967) - was tested with the R-17M / 8K14-1 rocket in 1962-1964, put into service together with the SPU 9P117 in 1967. could not be used on SPU 2P19. Sub-caliber warheads (such as R-17VTO warheads without aerodynamic rudders) could not be installed on a standard 8K14 rocket and the rocket needed to be upgraded (R-17M / 8K14-1), it was equipped with an ampoule power supply battery and contained a cylinder with OM. The initiating device - the 9B62 warhead control device - before the launch, the container with the OM was pressurized, and when the OM control device was triggered, it was sprayed into the atmosphere by displacement. The affected area is an elongated ellipsoid with an increase in concentration closer to the point where the warhead falls. Withdrawn from service in the 1980s.
OV type - mustard-lewisite mixture
Warhead mass - 1016 kg
Chemical warhead - case 8F44G / 8F44G-1 warhead "Tuman-3" (1964) is made in the dimensions of a standard warhead 8K14 rocket, but initially could only be used with the 8K14-1 rocket (because it used ampoule batteries 1SB25 / 1SB25M, and their use on warheads is possible only on this rocket model), later the warhead design was finalized and could also be used on 8K14. Passed tests in 1963-1964, was put into service instead of the chemical warhead 3N8. You can set the height of the charge. The initiating device is the I-214A safety actuator. By 1987, the 8F44G-1 modification was in service. Warheads are stored in container 9101-0/8F44G or 9101-0/8F44G-1. Can be used with any type of SPU. The cocking of the warhead took place after the engine was turned off, at the final stage of the trajectory, the radio altimeter issued a command to the PIM, which initiated the explosion of the warhead with the spraying of OM. The warhead was in service until 1997. As of 1987, 317 8F44G-1 warheads were in storage at the base in Shchuchye, the 8F44-1 warhead was shown in 1987 to Western observers in Shikhany.
Diameter - 884 mm
Warhead weight - 985 kg / 989 kg
The mass of the poisonous substance - 555 kg (8F44G / 8F44G1)
8F44G - nerve agent V of the first generation (in the form of a viscous substance)
8F44G-1 - third generation VX nerve gas (VR-33)
Chemical warhead with viscous soman - the creation of warheads was planned by the Decree of the Council of Ministers of September 11, 1961 using the new production capacities of factories in Volgograd, Novocheboksarsk and Pavlodar. Plans for the creation of warheads have not been implemented.
Nuclear warhead - case 9N33 charge RA17 (tests - 1964) - implosion-type plutonium charge, power 300 kt, replacement of nuclear warhead 8F14. Explosive device of special equipment DU-APR. Storage of warheads is carried out in container 9101-0A/8F14 (all modifications of warheads). In combat charge RA17 ball implosive charge diameter is smaller than in warhead 269A (at higher power), so the charge is placed closer to the nose of the warhead, and the warhead corus is sharper - this improved static
rocket stability and aerodynamics.
Length - 2870 mm
Midsection diameter - 884 mm
The center of gravity of the fully equipped warhead (from the end of the docking frame) - 933 mm
The angle of the semi-opening of the cone of the bow of the warhead - 9 degrees 30 minutes
Warhead body weight - 347 kg
Warhead weight - 989 kg
The maximum temperature inside the warhead case in flight is +50 degrees
Warhead temperature during storage - from +5 to +15 degrees C. (at air temperature below +5 degrees C, all 9H33)
Warhead temperature during storage - from +5 to +35 degrees C. (at air temperature above +5 degrees C, all 9H33)
Warhead body modifications:
9N33GVM - overall weight layout
9N33U, 9N33UT - training and training versions of the warhead
Nuclear warhead - body 9N33 charge RA17-2, charge modification RA17
Power - 300 kt
Nuclear warhead - body 9N33 charge RA17-3, charge modification RA17
Power - 300 kt
Nuclear warhead - case 9N33-1 charge RA104 - power 20 kt. Explosive device of special equipment DU-APR. Storage of warheads is carried out in container 9101-0A/8F14 (all modifications of warheads).
Warhead temperature during storage - from 0 to +15 degrees C. (when the air temperature is below 0 degrees C, all 9H33-1)
Warhead temperature during storage - from 0 to +35 degrees C. (at air temperature above 0 degrees C, all 9H33-1)
Warhead weight - 989 kg
Nuclear warhead - body 9N33-1 charge RA104-01 - power 200 kt. Explosive device of special equipment DU-APR.
Warhead weight - 989 kg
Thermonuclear warhead - housing 9N33-1 (9N33-1B) charge RA104-02 - power 500 kt. Explosive device of special equipment DU-APR.
Warhead weight - 989 kg
Nuclear warhead 407A14 in the case 8F14 with a capacity of 5 kt. It did not enter service. Explosive device of special equipment DU-APR.
High-explosive incendiary warhead 8F45 - experimental warhead, not adopted for service. VV - TGAG-5 with an active shell from the composition of AC-8 (substance with high temperature combustion).
Cassette warhead 8F44K, R & D started in 1970. It did not enter service or did not exist at all. Affecting submunitions - 42 pieces of 122 mm combat high-explosive fragmentation elements.
Volumetric detonating warhead (used by Soviet units in Afghanistan, 1979-1989, not confirmed - perhaps it means the explosion of a conventional warhead in combination with the remaining rocket fuel).
Nuclear 3 x MIRVs (1980s) - in the 1980s, R & D modifications were carried out with 3 x nuclear MIRVs (similar to the Pioneer MIRVed MRBMs (SS-20 SABER). The estimated power of one warhead is 100 kt. The total mass of the MIRVs It was supposed to be less than the mass of standard warheads, which should have led to an increase in range.It was possible that optical seekers were supposed to be used on the MIRV (speculation).Development was stopped at the design stage.No other data.
Note: the rocket can be equipped with warheads in a combat version or in a telemetric one, also all standard warheads have warheads of the main gun - overall weight mock-ups;
The layout of the complex 9K72(drawing from Zaloga Steven J., Scud Ballistic Missile and Launch Systems 1955-2005. Osprey Publishing. 2006):
The numbers indicate:
| 1 - Starting table reflector | 20 - Crew compartment / radio station |
| 2 - Starting table 9Н117 | 21 - Captures of the lifting ramp of the rocket (open) |
| 3 - Stabilizing support SPU | 22 - Rocket lifting ramp (lowered) |
| 4 - Control panel of the stabilization and launch system | 23 - Pump control cabin |
| 5 - Fire extinguisher | 24 - Oxidizer tank |
| 6 - Table raise/lower control panel | 25 - Fuel tank |
| 7 - Container with tools | 26 - Compartment of instruments of the control system 1 |
| 8 - Places for personnel in the control cabin | 27 - Explosive warhead |
| 9 - Prelaunch control cabin | 28 - warhead 8F44F |
| 10 - Air intake grille | 29 - Contact fuse |
| 11 - Crew seats | 30 - Bottom fuse |
| 12 - Cylinders of compressed air for starting the SPU engine | 31 - Compartment of instruments of the control system 2 |
| 13 - Cab steps | 32 - Cable channel |
| 14 - Driver's seat | 33 - Fuel supply hose to the engine |
| 15 - Headlight | 34 - Oxidizer supply pipe |
| 16 - Engine compartment | 35 - Engine turbocharger |
| 17 - Top part lifting ramp | 36 - Engine 9D21 |
| 18 - Engine air intake | 37 - Compressed air to start the fuel system |
| 19 - Radio station antenna |
Modifications and designations:
Complex 9K72 "Elbrus", rocket R-17 / 8K14,SPU 2P19 - SS-1B SCUD-A(1962) - operational-tactical missile, basic version - deep modernization of OTP R-11M (SKB-385). The oxidizer and fuel tanks were swapped compared to the R-11M, a new LRE with a turbopump unit was installed, and the control system was improved. the first version of the complex was based on the tracked SPU 2P19.
Section of the 8K14 / R-17 rocket (fig. KBM named after V.P. Makeev)
Complex 9K73, missile R-17V / 8K114(1963) - helicopter complex 9K73 with Mi-6RVK helicopter (1963). By Decree of the Council of Ministers of the USSR No. 135-66 of February 5, 1962, the development of the R-17V rocket-helicopter complex as part of a lightweight SPU and a Mi-10 helicopter began. The development was carried out by OKB-235 of plant No. 235 - the Votkinsk Machine-Building Plant, the chief designer was E.D. Rakov. In the course of work on the implementation of the R-17V project in 1963, the 9K73 complex was created with the Mi-6RVK helicopter, the 8K114 missile and the SPU 9P115. SPU was developed by GSKB / KBTM under the leadership of L.T. Bykov. A prototype SPU 9P115 was made in 1963, tests were completed in 1965. After testing in 1965, according to unconfirmed reports, the complex entered trial operation with the troops (it was not accepted for service). As of 1970, the complex was still in trial operation.
SS-1C SCUD-B (1965) - export modification / execution of R-17.
Complex 9K77 "Record", missile R-17M / 9M77 - SS-1D SCUD-C / KY-03(1965) - missile variant with larger tanks and a range of up to 500 km. Development on an initiative basis was carried out by OKB-235 (design bureau of the Votkinsk Machine-Building Plant) under the leadership of E.D. Rakov. The development was carried out under the ROC code "Record" in 1964-1968. The technical management of the project is entrusted to SKB-385 (V.P. Makeev) and SKB-626 (N.A. Semikhatov). The proposal to create a rocket was considered by the military-industrial complex under the Council of Ministers of the USSR and the development was started by the Decree of the Council of Ministers of the USSR of March 1963.
The rocket was created on the basis of the R-17 rocket design using a new type of fuel and a new rocket control system. Design range - 500 km. The head of the rocket was inseparable. With increasing range, the angle of approach of the missile to the target also decreased, especially at the limit
range, while the conical part of the warhead due to the lifting force created a pitching moment, which led to a significant deterioration in firing accuracy. The chief designer E.D. Rakov proposed to use the original design - the head part with a conical perforated shell and a reduced cone-cylindrical instrumental pressurized compartment. In this design, aerodynamics was provided along the cone, lift - along the cylinder inside it. Particular difficulties arose in the selection of material for the perforated cone - the proposed heat-resistant steel burned in the descending atmospheric section of the rocket's track. Due to the large number of perforations in the outer shell, the application of a thermal barrier coating was practically impossible.
Flight design tests of the 9K77 missile system took place at the Kapustin Yar test site from April 1964 to 1967. Colonel General I.I. Volkotrubenko was the Chairman of the State Commission. The tests were very successful, but the last four launches were successful and a total of 5 successful launches were carried out under the LKI program. The missile was identified by the US Department of Defense as KY-03 from satellite imagery.
Starting weight - 6370 kg (western data)
Warhead mass - 600-700 kg (western data)
Range - up to 450 km (western data)
In connection with the creation of OTP on solid fuel "Temp-S" with a flight range of up to 900 km, work on the R-17M complex was stopped. Later, due to disagreements with the director of plant No. 235 V.G. Sadovnikov, not without the participation of A.D. Nadiradze, a competitor of the 9M77 project, the chief designer of the rocket and complex E.D. Rakov was removed from development and soon fired ( east - Karpenko).
Complex 9K72, rocket R-17 / R-17U / 8K14-1(1967) - 8K14 rocket with design changes for the use of chemical warhead 3N8 (tests 1962-1964, put into service in 1967 together with SPU 9P117), in some sources the rocket is called R-17U. The missile was in service. Steel docking frame instead of aluminum, the ability to install heavier (more than 1000 kg) warheads. Air ducts of low and high pressure are connected along the body of the rocket to the cut of the instrument compartment (the plane of the docking of the rocket with the warhead). It can be used with any warheads, but with 3N8 warheads only on SPU type 9P117 (that is, it was not used on the tracked SPU 2P19).
R-17 target missile(1972) - by decision of the military-industrial complex under the Council of Ministers of the USSR, the Design Bureau of the Votkinsk Machine-Building Plant was developing a target missile based on the R-17 missile. The purpose of the target is to test anti-aircraft missile systems with limited missile defense capabilities. In the body of the warhead of the rocket, equipment with sensors was located and a special armored unit was installed to transmit data on the coordinates and type of damage to the warhead to the ground. Design documentation was developed in 1971-1972. In November-December 1972, target missiles were tested by three successful launches at the Emba test site. Target missiles are recommended for adoption and until 1977 were mass-produced in small batches at the Votsk Machine-Building Plant. Later, it is likely that regular R-17 missiles were converted into targets. target missiles were used to test the capabilities of the S-300 air defense system, and later the S-300PM at the Kapustin Yar training ground.
Rocket R-17 serial improvement- a version of a serial rocket modernized during production in Votkinsk (mid-1970s). The fuel storage time in a fueled rocket has been increased to 90 days (according to media reports) and up to 1 year when stored without starting fuel. Range not less than 270 km.
Complex 9K72-O (optical) "Aerophone", rocket R-17VTO / 8K14-1F - SS-1E SCUD-D / SCUD-C VTO (?) / SCUD-D(1979) - in 1967-1973 in TsNIIAG (Central Research Institute of Automation and Hydraulics) under the leadership of Z.M. Persits, together with the NPO Geophysics, R&D of an optical photo reference seeker (photo reference - a photograph of the terrain with the location of the target) was carried out for a product based on the 8K14-1 missile (project " Aerophone"). In 1974-75. a prototype of an optical seeker with digital data processing was created (a digital image of the area with a selection from a computer image library). In 1975-79. GOS were tested on the Su-17 aircraft.
Development tests missile system with the Aerofon warhead were launched at the Kapustin Yar test site as part of the first stage of testing (R&D theme "Flag") from November 1977 to September 1979. The warhead with the seeker was tested by launches on the OTR 8K14-1. The first launch of an 8K14-1 missile with a warhead with a working seeker was made on September 29, 1979. The launch range was 300 km, the KVO was several meters. In total, during the first stage of testing, 3 missile launches were carried out. A decision was made to create a serial military version of the Aerofon complex - contractors - TsNIIAG, PO Votkinsk Machine-Building Plant and PO Podolsky Machine-Building Plant.
The second stage of testing - factory flight design tests of the complex - took place from 1983 to 1986 (a total of 8 launches were made). September 24 and October 31, 1984 - unsuccessful launches. Since 1985, successful tests.
The third stage - state tests of the Aerofon complex, taking into account improvements and upgrades based on the results of the first two stages of testing - took place from March 1986 to September 1989. Chairman of the state commission, deputy head missile troops and artillery of the Leningrad Military District, Major General Alexei Petrovich Grobovoy. During the state tests, 22 launches of missiles with the Aerofon warhead were carried out. It was decided to accept the complex for trial operation and for study at higher educational institutions.
The complex was put into trial operation under the name 9K72-O in 1989. In September 1990, part of the 22nd missile brigade of the Belarusian Military District (composition - 381, 383, 397 orders, in total in the brigade 18 SPU 9P117M, Kremenchug, Dombovar, military unit 14359. Disbanded on May 3, 2005) arrived in Kapustin Yar to familiarize and conduct test launches of the 9K72-O Aerofon complex. The launches were carried out with test versions of missiles with white detachable parts and a standard version with green warheads. The first launch was made by a single rocket, the second launch was by a pair. The results - at a launch range of 150-200 km (judging by the launch trajectory and cut-off time of the engines), the CVO ranged from 2-6 m to a little over 10 m. The launches were made in clear weather. In 1993, for trial operation, he entered the 22nd missile brigade complete with automated system strike control 1U120 "Viskoza" (although there is unconfirmed information about the disbandment of the brigade in 1992) and in the 1990s the complex was offered for export. The complex was not adopted for service due to the high meteorological dependence of the GOS (cloudiness). As of 2008, the 9K72-O complexes are stored in one of the missile brigades.
R-17VTO projections
(Shirokorad A.B., Atomic ram of the twentieth century. M., Veche, 2005)
Rocket "R-17VTO2"- conditional name, modification of the 8K14 missile with a radar homing system. According to unconfirmed data, R&D of such a system was carried out. Probably, R&D has not been brought to testing, development has (probably) been discontinued. There is no exact data on the GOS (i.e., maybe the GOS was a passive radar, or maybe a radar-GOS with guidance from a digital map of the area or some other principle).
R-17(rocket index - 8K14, according to the classification of the US Defense Ministry and NATO - SS-1c Scud B, export designation R-300, unofficially - "kerosene stove") - a Soviet liquid-propellant single-stage ballistic missile on long-term fuel components, which is part of the operational-tactical missile system 9K72 Elbrus.
History of creation
Attempts to further modernize the R-11M missiles (project R-11MU, index GRAU 8K12) showed the inexpediency of using a displacement fuel supply system to increase the specific thrust of the engine (in order to increase the missile range over 150 km with a payload mass of at least 900 kg). The low thrust reserve of the engine did not allow increasing the stock of rocket fuel components (and hence the total mass of the rocket), while further increasing the pressure in the tanks was also impossible due to reaching the limit value.
The best solution to the problem was to use an engine with a turbopump fuel supply system. In addition, the turbopump unit provided better engine “controllability” (due to precise thrust control), which means that real opportunity improve the accuracy of the rocket (in range).
By 1957, in OKB-3 NII-88, chief designer D. D. Sevruk, an LRE with TNA C3.42 was developed, which could be used in missiles with R-11 dimensions, while guaranteeing a maximum range of about 240 km.
At the suggestion of the initiative group, the chief designer of SKB-385 V.P. Makeev decided to prepare, by January 10, 1958, a design layout drawing, a pneumohydraulic scheme and basic calculations for a new rocket. In OKB-1, S.P. Korolev supported this project, thanks to which this idea also found support in the GAU (Main Artillery Directorate). By Decree of the Central Committee of the CPSU and the government No. 378-181 of April 1, 1958, SKB-385 was entrusted with the development of the R-17 rocket (with a turbopump fuel supply system) with a firing range of 50 to 240 km.
The new R-17 rocket was assigned the index 8K14 in the GAU, Lieutenant Colonel A. V. Titov was appointed to lead the product, and Lieutenant Colonel P. V. Zakharov was appointed to lead the control system.
The developers of the main R-17 systems from related industry organizations were appointed:
for the on-board control system - chief designer of NII-592 N. A. Semikhatov;
for the engine (C3.42) at the first stage of flight tests - the chief designer of OKB-3 NII-88 D. D. Sevruk;
for the engine (C5.2) from the second stage of flight tests - the chief designer of OKB-5 A. M. Isaev;
for gyroscopic instruments (1SB9, 1SB10, 1SB12) chief designer of NII-944 V. I. Kuznetsov;
for explosive charge and conventional warhead equipment (8F44) - NII-6;
for a special charge and a set of electrical automation MS 8F14 - scientific supervisor of the NII-1011 MSM Yu. B. Khariton, chief designer S. G. Kocharyants;
for the complex of ground equipment - the chief designer of the GSKB V.P. Petrov;
for aiming instruments (8Sh18) - chief designer of plant 784 of the Kyiv Council of National Economy S.P. Parnyakov;
for the caterpillar launcher (2P19) - chief designer of the OKBT of the Leningrad Kirov Plant Zh. Ya. Kotin;
on the starting unit on wheels (2P20) - the chief designer of the Central Design Bureau TM Krivoshein.
To speed up the process of developing the complex, the weight and size characteristics of the new missile were chosen close to those of the R-11M. Thus, it was possible to partially use ground equipment units from the 8K11 rocket as part of the new complex (however, certain improvements were required).
Despite the outward similarity of the R-17 with the R-11M, structurally these missiles have little in common: in fact, the layout scheme was completely changed, a more advanced control system was developed, a fundamentally different pneumohydraulic system was used, a method of refueling rocket fuel components and so on.
In the process of working on the R-17 rocket, OKB-5 (headed by the chief designer A. M. Isaev) developed a new engine with improved performance. Thanks to the higher thrust of the new engine, it was possible to increase the maximum range of the rocket.
The first test launch of the R-17 rocket took place at the Kapustin Yar (KapYar) test site on December 12, 1959.
At the first stage of development, prototype missiles were manufactured at the Zlatoust Machine-Building Plant, but at the second stage of flight tests, the manufacture of products (and subsequently mass production) was transferred to Votkinsky mechanical plant(No. 385), which already produced the R-11M (8K11).
On the initial stage development of a nuclear warhead, it was supposed to use a 5 kiloton charge in the 8F14 case (warhead 407A14), similar to that used in the 407N bomb, which was being developed at the same time. However, later a more powerful charge (10 kt) was developed with better weight and size characteristics (primarily smaller in weight, thanks to which it was possible to further increase the range of the rocket) and the 269A warhead was adopted in the same building (8F14).
For the transportation and launch of missiles, the 2P19 tracked chassis based on the ISU-152 was developed, outwardly similar to the launch unit 2U218 of the R-11M rocket. Four 2P19 caterpillar launchers with R-17 missiles took part in a military parade on Red Square on November 7, 1961.
On March 24, 1962, by a decree of the Council of Ministers of the USSR, the R-17 rocket was adopted by the Soviet Army.
The 2P20 launcher on the MAZ-537 wheeled chassis (developed simultaneously with the tracked 9P19) did not pass the test and was not accepted into service. In 1967, the 9P117 launcher on the MAZ-543P four-axle self-propelled chassis was put into service.
In the 1960s the rules for indexing weapons were revised in order to streamline them. It was then that the missiles were no longer assigned the “K” index, which was replaced by the “M” index (moreover, the name of the complex began to differ from the name of the rocket by only one letter). However, for missiles that were already in service (including 8K14), the indexing remained the same, but new indices were assigned for missile systems (which had not previously had separate indices). The complex of the 8K14 rocket with a set of equipment and technology that ensures its operation received the index 9K72.
The basic R-17 model was intended primarily for use with nuclear warheads, since insufficient accuracy did not guarantee the effectiveness of the use of high-explosive warheads (8F44 warheads were produced in smaller volumes than nuclear warheads, and were primarily exported complete with missiles R-17E).
Later, chemical warheads were created for the 9K72 complex, for which a modification of the 8K14-1 missile was developed (which gradually replaced the basic modification 8K14). Accordingly, the launchers were also modernized.
During the operation of the 9K72 complex, the Customer (Ministry of Defense) repeatedly raised questions about the need for modernization to increase its combat effectiveness. To this end, relevant R&D was carried out and attempts were made to develop new modifications of the complex (for example, 9K73 - with a lightweight launcher transported by helicopter, 9K77 - with an increased range, 9K72-1 - with a detachable warhead controlled in the final section of the trajectory using optical homing heads and others). However, none of these modifications was accepted into service.
In the 1970s, the Votkinsk plant produced small batches of La-17M (5S1Yu) target missiles developed on the basis of the R-17, which were used in the development of anti-aircraft missile systems. In 1995, 2001 and 2002 when testing the S-300 anti-missile system and its modifications, serial 8K14 combat missiles were used as targets.
Design
Main characteristics of the product
|
The length of the product from the support feet to the top of the head |
|
|
Product body diameter |
|
|
Span over stabilizers |
|
|
Weight of unfilled product with 269A head |
|
|
Fully loaded weight with 269A head |
|
|
Engine 9D21 |
liquid, reactive |
|
Supply of fuel components to the engine |
Turbopump unit powered by a gas generator |
|
THA promotion method |
From a powder bomb |
|
Weight of unfilled product with head part 8Ф44 |
|
|
The weight of a fully filled product with a head part 8Ф44 |
|
|
Engine Fuel Components: |
|
|
starting fuel |
|
|
main fuel |
|
|
oxidizer |
|
|
Method of ignition of fuel components |
Chemical (self-ignition) |
|
Filling the product with fuel components: |
|
|
oxidizing agent |
|
|
main fuel |
In the horizontal position of the product |
|
starting fuel |
In the vertical position of the product on the starting unit |
|
The nature of the filling |
Volumetric weight |
|
Refueling weight of fuel and compressed air at a temperature of +15°С |
|
|
Including: |
|
|
weight of AK-27I oxidizer |
|
|
fuel weight TM-185 |
|
|
starting fuel weight TG-02 |
|
|
compressed air weight |
|
|
Control system |
Autonomous inertial |
|
Executive element of the control system |
gas rudders |
|
Emergency detonation system |
Autonomous |
|
Minimum range |
|
R-17 used TM-185 (based on petroleum products: polymer distillate - 56%, light pyrolysis oil - 40%, tricresol - 4%) and AK-27I (based on nitric acid) as the main components of the R-17 fuel. As a starting fuel - TG-02 "Samin".
It has a maximum range of 300 km. The missiles could carry both a conventional high-explosive and a nuclear warhead (in the 1960s and 1970s, five types of nuclear warheads with a capacity of 10, 20, 200, 300 and 500 kt were developed at VNIITF and put into service).
Warheads in chemical equipment (3N8, 8F44G and 8F44G1) were called "special warheads", since the USSR officially denied the presence of chemical weapons in service. The modification of the 8K14-1 rocket had additional pipelines to activate the ampoule batteries of the warhead and refuel the warhead pneumatic block with air in preparation for launch. The front docking frame, made not of duralumin, but of steel, made it possible to use heavier warheads with “non-standard” (with a shape different from the cone) geometry, such as 3N8 (and later - 9N78 with GOS).
In addition, the 8K14-1 rocket had some differences in operation (in particular, it had factory-installed gas-jet rudders,
which eliminated the need for assembly operations with rudders in the technical position).
In countries that produced 8K14 under license, developments were carried out to increase the range of the rocket (mainly by reducing the weight of the warhead. In particular, a modification was developed in the DPRK in which, by reducing the combat load, the capacity of the fuel tanks was increased and, accordingly, the flight range increased missiles.At the same time, the accuracy of the missile has deteriorated by almost half compared to the Soviet original.Western intelligence was aware of the work on increasing the range of the R-17 missile, which was carried out in the USSR, and it was erroneously assumed that the complex with an increased range (9K77) entered service with the Soviet army.All developments of modifications of the R-17 with an increased range in Western literature received the designation Scud-C.
Further development of the model is also known under the Korean name "Nodong-1" ("Labor-1"). The first successful test was carried out by the DPRK in 1993 with improved firing accuracy. This modification often appears in foreign sources under the designation Scud-D (as well as 9K72-1 with GOS, developed in the USSR under the Aerophone project). However, it should be noted that these designations are not official and may be used inaccurately in various sources. In addition, there are a significant number of 8K14 modifications even within the specified series, and therefore the data below should be considered indicative.
In the USSR, work was carried out (ROC "Aerofon") to improve the accuracy of the missile system by creating a detachable guided warhead in conventional equipment 9N78 (weighing 1017 kg) with an optical homing head 9E423 (an 8K14-1 missile docked with a 9N78 warhead received the index 8K14-1F ). The 9F59 interface kit was installed on the launchers. The modified missile system, equipped with a 9S751 data preparation machine, a 9S752 data entry machine, a 9B948 routine maintenance machine, a set of arsenal equipment 9F820, etc., was named 9K72-1 (some sources erroneously indicate the index 9K72O, where "O" is optical). The maximum range for the 8K14-1F missile was 235 km, and the accuracy was 50-100 m (depending on the scale of aerial photographs used in the preparation of the standard). The complex was accepted into experimental military operation (order of the USSR Ministry of Defense No. 026 of 1990), but was not accepted into service (due to poor accuracy in conditions of insufficient visibility and strong dependence on other conditions).
Comparative performance characteristics
Tactical and technical characteristics
|
R-17M? (9K77) |
R-17VTO (9K72-1) |
"El Abbas" |
||||
|
Country |
|
|
|
|
|
|
|
GRAU index |
||||||
|
NATO code |
||||||
|
Length, m |
||||||
|
Diameter, m |
||||||
|
Takeoff weight, kg |
||||||
|
Propulsion system |
Single stage, liquid |
|||||
|
Firing range, km |
||||||
|
KVO, m |
||||||
Combat use
R-17, put into service in 1962, after it completed the missile brigades of the ground forces of the USSR, the armies of the countries participating in the Warsaw Pact, and other social. countries, was actively exported in a non-nuclear version (the rocket was not supplied to China due to the deterioration of Soviet-Chinese relations). Export R-17 (R-17E or R-300) and its modifications were repeatedly used in regional conflicts.
The North Korean, Pakistani, and Iranian missile programs have used R-17 technology to build their medium-range missiles.
Doomsday War (1973)
A small number of P-17s were used by Egypt against Israel during the 1973 war.
Iran-Iraq War (1980-1988)
About 600 R-17s and their modifications were used to shell cities by both Iraq and Iran during the Iran-Iraq war (the so-called "war of the cities"). The Iraqis developed longer-range missiles based on the R-17 - Al Hussein (missile) and Al-Abbas.
War in Afghanistan (1979-1989)
More than 2,000 missiles were used by the Soviet army in the Afghan war.
Gulf War (1991)
During the Gulf War in 1991, the Iraqis fired on Israeli territory with modified P-17s (40 missiles) and Saudi Arabia(46 missiles) (according to other sources, 98 missiles were launched). In general, the effectiveness of these rocket attacks was insignificant - according to the Israeli side, two-thirds of the launched rockets fell in uninhabited territory, 2 people became victims of rocket attacks on Israeli territory, and 11 more were seriously injured. Only one attack had a significant result - a rocket hit the American barracks in the city of Dharam, as a result of which 28 American soldiers were killed and another two hundred were injured.
The military inspects a Scud-type missile shot down in the desert by the MIM-104 Patriot air defense system
American forces were used to repel the attacks. anti-aircraft missile systems"Patriot", the effectiveness of which there are conflicting statements. According to Israeli data, no more than 47 Scuds fell into the Patriots' coverage areas, at which a total of 158 anti-missiles were fired. According to the Israeli Ministry of Defense, the Patriots, despite the overexpenditure of anti-missiles (including the case with the consumption of 28 units per target), managed to intercept no more than 20% of the missiles launched by the Iraqis. In other sources, the data vary greatly (from 9% according to the estimates of the US Administration Control Chamber to 36% in Russian sources, American sources now indicate numbers up to 52-80%, during the war, figures up to 100% were also called). Such different data are related to the objective complexity of assessing the results of firing - even close detonations of the Patriot missiles did not destroy the R-17 warheads, but only diverted them from the course. Under these conditions, given the low inherent accuracy of the R-17 missiles, the criterion for classifying the affected missiles as "downed" missiles is subjective. However, taking into account the fact that one R-17 missile is three times cheaper than one Patriot missile, the economic damage to the United States was inflicted.
Yemeni Civil War (1994)
During the 1994 Yemeni civil war, both South Yemeni separatists and government armed forces used R-17 missiles.
Second Chechen War
In September 1999, on the basis of the 60th training center for the combat use of missile forces of the ground forces (military unit 42202, Kapustin Yar, site 71), military unit 97211 (630th separate missile division) was formed to participate in hostilities in the Caucasus , which was armed with the 9K72 missile system. The division commander, Lieutenant Colonel Zakharchenko I. I. The 630th order was stationed in the area of the former village of Russkaya on the border with Chechnya, and during the course of hostilities from October 1, 1999 to April 15, 2001, made 250 launches of 8K14-1 missiles. Missiles were fired, including expired ones, while not a single failure was recorded. After the stock of missiles was used up, the division handed over the equipment to the storage base and in April 2001 was redeployed to the 71st site of the Kapustin Yar training ground. In 2005, the 630th order was the first in the Russian Federation to receive the 9K720 Iskander complex.
North Korea - more than 30 Scud-B / C launchers and up to 200 missiles
Vietnam - some Scud-B
Afghanistan - since 1989, RK 9K72 has been in service with the missile battalion of the Special Purpose Guard of the Ministry of State Security of the Republic of Afghanistan.
Withdrawn from service
Since 1988, the production of 8K14 (8K14-1) missiles at the Votkinsk plant has been discontinued. Taking into account the fact that the technical service life of a rocket is 22 years (gyro-devices are subject to replacement after 20 years of operation), at present the technical service life of all rockets produced at the Votkinsk plant has expired. This is the main reason for the removal of R-17 missiles from service.
In addition, the United States considers Scud missiles as "weapons of mass destruction" (one of the components nuclear weapons- a carrier, since the R-17 missile is capable of carrying a warhead weighing up to a ton, which makes it possible to use it to deliver even obsolete second-generation nuclear weapons), and therefore active efforts are being made (by political pressure and financial interest) to destroy those available in the world Scud complexes. Thus, the United States financed the destruction of the 9K72 complex in Ukraine, assisted in the destruction of equipment and equipment of the 9K72 complex in Hungary, Bulgaria [approx. 1], also plan to finance the destruction of 8K14 in Libya.
Belarus- 60 launchers, the complex was decommissioned, the 22nd mixed missile brigade, which was armed with 9K72, was disbanded on May 3, 2005.
Bulgaria, was in service with:
46th missile (artillery technical) brigade (Samokov) - the complex was decommissioned and liquidated in 2002. According to some data, 64 missiles were destroyed.
129th missile (artillery technical) brigade (Karlovo) - as of 1989
66th missile (artillery technical) brigade (Yambol) - as of 1989
Hungary, was in service with the MN 1480 (from the 5th mixed missile brigade) Tapolca (Hung. Tapolcá). MN 1480 ceased to exist in 1990, and in May 1995, the destruction (mainly by demolition) of the existing equipment and equipment of the 9K72 complex was completed. The last of the eight 9P117M1 launchers is currently on display in the park-museum military history in Kezel.
Romania, was in service with:
32nd operational-tactical missile brigade (Tekuch) - as of 1989
37th operational-tactical missile brigade (Ineu) - as of 1989
Ukraine- the complex was decommissioned in 2007; on April 12, 2011, its disposal was completed. According to some sources, 185 military missiles, 50 launchers and other equipment and equipment were disposed of (at the expense of US funding). At the same time, according to the statement of the Ukrainian side, until 1998 there were 117 Scud launchers in Ukraine, and 63 of them were dismantled by Ukraine at its own expense until 2005.
Czechoslovakia, was in service with:
- 331st operational-tactical missile brigade (Yichin) - as of 1989
311th operational-tactical missile brigade (Yintse (English) Russian) - as of 1989
321st operational-tactical missile brigade (Rokytsani) - as of 1989
In March 1962, the 9K72 Elbrus operational-tactical missile system was adopted by the Soviet Army. Over the past half century, the complex, which received the NATO designation SS-1C Scud-B (Scud - "Gust of Wind", "Squall"), managed to take part in a number of military conflicts, from the Doomsday War (1973) to the second Chechen campaign in 1999 -2000 years. Moreover, the R-17 missile, which is the basis of the Elbrus complex, for several decades abroad has been a kind of standard ballistic target for tactical missile defense systems - almost always missile defense capabilities are evaluated precisely by the ability to intercept Scud-B missiles.
of the Elbrus complex began in 1957, when the Russian military wanted to get an upgraded version of the R-11 ballistic missile. Based on the results of studying the prospects for improvement, we decided that it would be wiser to take advantage of the existing developments and create a completely new design based on them. This approach promised a twofold increase in the range of the missile. At the end of February 58, the Military-Industrial Commission under the Council of Ministers and the Council of Ministers issued resolutions necessary to start work in this direction. The creation of a new rocket was entrusted to SKB-385 (now the State Missile Center, Miass), and V.P. Makeev. In September of the same year, a preliminary design was ready, and by the end of November, all design documentation had been collected. Until the end of 1958, preparations began at the Zlatoust Machine-Building Plant for the manufacture of the first rocket prototypes. In May of the following 1959, the GAU of the Ministry of Defense approved the requirements for new rocket and assigned it the index 8K14, and the entire complex - 9K72.
The assembly of the first missiles began in mid-1959, and flight tests began at the Kapustin Yar test site in December. The first stage of testing ended on August 25, 1960. All seven launches were successful. Shortly thereafter, the second stage of testing began, during which 25 launches were made. Two of them ended in an accident: during the first flight, the R-17 rocket with the C5.2 engine flew in the opposite direction from the target, and the third ended in self-destruction of the rocket due to a short circuit in the active flight segment. The tests were considered successful and the 9K72 Elbrus operational-tactical missile system with the 8K14 (R-17) missile was recommended for adoption. On March 24, 1962, the recommendation was implemented by the corresponding resolution of the Council of Ministers.
The composition of the complex
The basis of the 9K72 complex is a single-stage ballistic missile 8K14 (R-17) with an inseparable warhead and a liquid engine. One of the measures to increase the range of the rocket was the introduction of a pump into the fuel system of the rocket to supply fuel and oxidizer. Thanks to this, the pressure inside the tanks, necessary for optimal engine operation, decreased by more than six times, which, in turn, made it possible to lighten the design due to thinner walls of the fuel system units. With the help of separate pumps, fuel (starting TG-02 "Samin" and the main TM-185), as well as the oxidizer AK-27I "Melange" is fed into a single-chamber rocket engine S3.42T. To simplify the design of the engine, it is started using starting fuel, which ignites on its own upon contact with an oxidizing agent. The approximate thrust of the C3.42T engine is 13 tons. The first series of R-17 missiles were equipped with S3.42T liquid-propellant rocket engines, but since 1962 they began to receive a new power plant. The C5.2 single-chamber engine received a different design of the combustion chamber and nozzle, as well as a number of other systems. The engine upgrade entailed a slight (by about 300-400 kgf) increase in thrust and a gain in weight of about 40 kg. The C5.2 rocket engine operated on the same fuel and oxidizer as the C3.42T.
The control system is responsible for the flight path of the R-17 rocket. Inertial automation stabilizes the position of the rocket, and also makes adjustments to the direction of flight. The missile control system is conditionally divided into four subsystems: motion stabilization, range control, switching and additional equipment. The motion stabilization system is responsible for maintaining the programmed course; for this, the 1SB9 gyrohorizon and the 1SB10 gyroverticant collect information about the rocket accelerations along three axes and transmit it to the 1SB13 calculating and decisive device. The latter issues commands to steering machines. In addition, the control automation can issue a command to the automatic missile detonation system if the flight parameters differ significantly from the specified ones, for example, the deviation from the required trajectory exceeds 10 °. To parry emerging drifts, the rocket was equipped with four gas-dynamic rudders installed in the immediate vicinity of the engine nozzle. The range control system is based on the 1SB12 calculator. Its tasks include monitoring the speed of the rocket and giving a command to turn off the engine when it reaches the desired one. This command terminates the active flight mode, after which the missile reaches the target along a ballistic trajectory. The maximum range of the missile is 300 kilometers, maximum speed on the trajectory - about 1500 meters per second.
A warhead was mounted in the bow of the rocket. Depending on the tactical need, one of several options could be used. The list of main warheads for the R-17 looks like this:
- 8F44. high explosive head part weighing 987 kg, approximately 700 of which were TGAG-5 explosives. The high-explosive warhead for the R-17 is equipped with three fuses at once: a nasal contact fuse, a bottom barometric fuse for detonation at a certain height, and a self-destruct fuse;
- 8F14. Nuclear warhead with an RDS-4 charge with a capacity of ten kilotons. A training version of 8F14UT was produced without a nuclear warhead;
- chemical warheads. They differed from each other in the amount and type of poisonous substance. So, 3N8 carried about 750-800 kg of mustard-lewisite mixture, and 8F44G and 8F44G1 each carried 555 kg of V and VX gas, respectively. In addition, it was planned to create an ammunition with viscous soman, but the lack of production space did not allow the development to be completed;
- 9N33-1. Thermonuclear warhead with a charge of RA104-02 with a capacity of 500 kilotons.
The main element of the ground equipment of the Elbrus complex is the launch unit (launcher) 9P117, developed at the Central Design Bureau of Transport Engineering (TsKB TM). The wheeled vehicle is designed for transportation, pre-launch checks, refueling with starting fuel and directly launching the R-17 rocket. All units of the launcher are mounted on a four-axle MAZ-543 chassis. The launch equipment of the 9P117 machine consisted of a launch pad and a lifting boom. These nodes are fixed on the axis and can be rotated 90 °, transferring the rocket from a horizontal transport to a vertical launch position. The rocket is lifted using a hydraulic cylinder, other mechanics of the boom and table are driven by electromechanical drives. After lifting to a vertical position, the R-17 rocket rests with its back on the details of the launch pad, after which the boom is lowered back. The launch pad has a frame structure and is equipped with a gas baffle shield, which prevents damage to the structure of the undercarriage of the 9P117 machine by hot gases from the rocket engine. In addition, the table can rotate in a horizontal plane. In the middle part of the starting unit 9P117, a cabin is installed with additional equipment and jobs for three people at the rate of the complex. The equipment in the wheelhouse is mainly designed to provide start-up and control over the operation of various systems.
In addition to the rocket and the launcher, the Elbrus complex included several other machines for various purposes. Because of this, the composition of the missile division looked like this:
- 2 launch vehicles 9P117;
- 5 command and staff vehicles based on the GAZ-66;
- 2 topographic surveyors 1T12-2M on the GAZ-66 chassis;
- 3 washing and neutralization machines 8T311 based on ZiL trucks;
- 2 tankers 9G29 (based on ZiL-157) with two refuelings of the main fuel and four launchers on each;
- 4 tank trucks for the oxidizer AKTs-4-255B based on the KrAZ-255 truck, each carrying two Melange filling stations;
- 2 truck cranes 9T31M1 with a set of related equipment;
- 4 2T3 soil carts for transporting a stock of missiles and 2 2Sh3 containers for combat units;
- 2 special vehicles based on "Ural-4320" for the transportation of warheads;
- 2 cars Maintenance MTO-V or MTO-AT;
- 2 mobile control points 9С436-1;
- material support platoon: tankers for cars, field kitchens, auxiliary trucks, etc.
Modifications
Without waiting for the complex to be put into service, the Central Design Bureau TM began to develop an alternative 2P20 launcher based on the MAZ-535 chassis. Due to insufficient structural strength, this project was canceled - no one saw the point in strengthening one chassis in order to replace another with sufficient strength and rigidity. Slightly more successful was the "Object 816" on tracked chassis Design Bureau of the Leningrad Kirov Plant. However, the production of this self-propelled launcher was limited to only an experimental batch of several units. Another original project of an alternative launcher reached the stage of trial operation, but was never put into service. The 9K73 installation was a lightweight four-wheeled platform with a lifting boom and a launch pad. It was understood that such a launcher could be delivered by an aircraft or helicopter of the appropriate carrying capacity to the desired area and from there launch a missile. During the tests, the experimental platform showed the fundamental possibility of rapid landing landing and firing of a ballistic missile. However, in the case of the R-17, it was not possible to use the full potential of the platform. The fact is that in order to launch and guide a missile, the calculation needs to know a number of parameters, such as the coordinates of the launcher and target, the meteorological situation, etc. In the mid-sixties, the determination of these parameters required the participation of specialized complexes on an automobile chassis. In addition, such preparation significantly increased the time required for launch. As a result, the 9K73 was not put into service and the idea of a "stripped down" light airborne launcher was not returned to.
Rocket 8K14 of the 9K72 complex with SPU 9P117 (photo by V.P. Makeev Design Bureau)
The situation was similar with the new modifications of the R-17 rocket. Its first modernized version was to be the R-17M (9M77) with increased capacity tanks and, as a result, a longer range. The latter, according to initial calculations, was to reach 500 kilometers. In 1963, at the Design Bureau of the Votkinsk Machine-Building Plant under the leadership of E.D. Rakov began designing this rocket. The original R-17 was taken as the basis. To increase the range, it was proposed to replace the engine and type of fuel, as well as to carry out a number of alterations in the design of the rocket itself. Calculations have shown that while maintaining the existing principle of flight to the target and further increasing the range, the angle between the vertical and the trajectory of the missile decreases on approach to the target. At the same time, the conical nose fairing of the rocket created a noticeable moment for pitching up, because of which the rocket could significantly deviate from the target. To avoid such a phenomenon, a new warhead was designed with a perforated fairing and a cylindrical casing of equipment and warhead inside. Such a system made it possible to combine both good aerodynamics in flight and almost completely eliminate the tendency of the rocket to pitch up. At the same time, I had to tinker with the selection of the type of metal for the fairings - the previously used ones could not withstand the temperature loads in the final flight segment, and the perforation of the fairing did not give a protective coating. Under the name 9K77 "Record", the updated operational-tactical missile system was sent to the Kapustin Yar test site in 1964. Test launches were generally successful, but still there were enough problems. The tests were completed only in 1967, when the R-17M project was closed. The reason for this was the appearance of the Temp-S missile system, capable of hitting targets at a distance of up to 900 kilometers.
In 1972, the design bureau of the Votkinsk Machine-Building Plant was given the task of making a target based on the R-17 missile for testing new anti-aircraft missile systems with limited anti-missile defense capabilities. The main difference between the target and the original missile was the absence of a warhead and the presence of a number of specialized systems for collecting and transmitting information about flight parameters and the course of interception to the ground. It is noteworthy that in order to avoid premature destruction, the main equipment of the target missile was placed in an armored box. Thus, the target, even for some time after the defeat, could maintain contact with ground equipment. Until 1977, R-17 target missiles were mass-produced; later, they were probably converted from mass-produced missiles with an ending warranty period.
Complexes 9K72 with SPU 9P117M on the march (photo by KBM named after V.P., Makeev)
Since 1967, specialists from the Central Research Institute of Automation and Hydraulics (TsNIIAG) and NPO Gidravlika have been working on the creation of photo reference guidance systems. The essence of this idea is that an aerial photograph of the target is loaded into the homing head and the target, having entered a given area, is guided using an appropriate computer and a built-in video system. Based on the results of the research, the Aerofon GOS was created. Due to the complexity of the project, the first test launch of the R-17 missile with such a system took place only in 1977. The first three test launches at a distance of 300 kilometers were completed successfully, conditional targets were hit with a deviation of several meters. From 1983 to 1986, the second stage of testing took place - eight more launches. At the end of the second stage, state tests began. 22 launches, most of which ended in the defeat of a conditional target, became the reason for the recommendation to accept the Aerofon complex for trial operation. In 1990, servicemen of the 22nd missile brigade of the Belarusian Military District went to Kapustin Yar to get acquainted with the new complex, called 9K72O. A little later, several copies were sent to the brigade. There is no information about the trial operation, moreover, according to various sources, the 22nd brigade was disbanded before the expected date for the transfer of missile systems. According to reports, all unused missiles and equipment of the complexes are in storage.
Service
The first batches of 9K72 Elbrus complexes entered service with the Soviet army. After completing the domestic armed forces, Elbrus was finalized for deliveries abroad. The R-17 missile went abroad under the designation R-300. Despite the large number of 9K72 in the Warsaw Pact countries, Egypt was the first to use it in practice. In 1973, during the so-called. During the Yom Kippur Wars, the Egyptian military fired several P-300 missiles at Israeli targets in the Sinai Peninsula. Most of the fired missiles hit the target without exceeding the calculated deviation. However, the war ended with an Israeli victory.
SPU 9P117 from the 112th missile brigade of the GSVG (Gentsrode, 1970-1980s, photo http://militaryrussia.ru)
The following facts of the combat use of R-17 missiles occurred during the war in Afghanistan. Operational-tactical missiles proved to be useful in attacks on Dushman fortifications or camps. According to various sources, Soviet rocket launchers made from one to two thousand launches, while several characteristic features operation. So, the deviation from the target, which reached a hundred meters at the 8K14 rocket, sometimes did not allow it to reliably hit targets with a blast wave and shrapnel. For this reason, already in combat units, a new method of applying ballistic missiles. Its essence was to launch a rocket at a relatively short range. The engine was switched off relatively early, and some fuel remained in the tanks. As a result, hitting the target, the rocket sprayed around itself a mixture of TM-185 fuel and AI-27K oxidizer. The expansion of liquids with subsequent ignition significantly increased the area of damage. At the same time, in a number of cases, the remnants of fuel and oxidizer caused a long-term fire in the shelled area. This ingenious method of using a missile with a standard HE warhead has given rise to rumors of the existence of some sort of volumetric explosion warhead. However, the existence of such a charge for the Elbrus complex has no documentary evidence.
Shortly after the first use of Elbrus in Afghanistan, he took part in the Iran-Iraq war. It is worth noting that R-300 missiles were launched by both sides of the conflict, although in different numbers. The fact is that Iraq bought export versions of the 9K72 complex directly from the USSR, and Iran acquired them through Libya. According to various sources, Iraq fired from 300 to 500 R-300 missiles at targets in Iran. In 1987, tests began on the Al Hussein missile, which is an Iraqi upgrade of the R-300. The Iraqi development had a lightweight warhead weighing 250 kg and an increased launch range - up to 500 kilometers. The total number of El-Hussein rocket launches is estimated at 150-200. The response to the Iraqi shelling was the purchase by Iran from Libya of a number of similar Elbrus complexes, but their use was on a much smaller scale. In total, about 30-40 missiles were fired. Just a few years after the end of the Iran-Iraq war, export R-300 missiles again took part in the hostilities. During Operation Desert Storm, the Iraqi military carried out attacks on targets in Israel and Saudi Arabia, and also fired on advancing American troops. During this conflict, the US military was able to put into practice the new Patriot anti-aircraft missile systems, which have limited missile defense capabilities. The result of the interception attempts is still a matter of controversy. Various sources give figures from 20% to 100% of destroyed missiles. At the same time, only two or three missiles caused significant damage to the enemy.
Reloading of the 8K14 rocket from the 2T3M1 transport vehicle to the 9P117M SPU using the KS2573 truck crane, 22nd RBR of the Belorussian Army, Tsel settlement, 1994-1996. (photo from the archive of Dmitry Shipuli, http://military.tomsk.ru/forum).
In the nineties of the last century, the 9K72 Elbrus complexes were almost never used in combat. No more than two dozen missiles were fired during several local conflicts. One of the latest uses of R-17 missiles refers to the second Chechen campaign. There is information about the formation in 1999 of a special unit armed with Elbrus. Over the next year and a half, Russian rocket scientists made two and a half hundred launches, including missiles with an expired warranty period. No major problems were recorded. According to reports, in the spring of 2001, the 9K72 complexes were transferred for storage.
With the exception of the former Soviet republics, which got the Elbrus complexes after the collapse of the USSR, the R-17 and R-300 operational-tactical missiles were in service with 16 countries, including Afghanistan, Bulgaria, Vietnam, East Germany, North Korea, Libya, etc. .d. After the demise Soviet Union and the Warsaw Pact, part of the missiles produced ended up in the steel independent countries. In addition, Russia's loss of its former positions in the international arena led to the fact that, with the direct assistance of NATO countries, some operators of the Elbrus complexes removed them from service and disposed of them. The reasons for this were the approaching end of the service life of the missiles, as well as the pressure of Western states, which still consider the 9K72 an object of increased threat: the possibility of installing even obsolete nuclear warheads on the missile affects. However, in some countries, the Elbrus complexes are still in service and in operation. Their number is small and constantly decreasing. It seems that within the next few years one of the oldest operational-tactical missile systems will be completely decommissioned throughout the world.
According to the websites:
http://rbase.new-factoria.ru/
http://vpk-news.ru/
http://militaryrussia.ru/
http://janes.com/
http://kapyar.ru/
http://rwd-mb3.de/
http://engine.aviaport.ru/
http://globalsecurity.org/
This system was designed in KB them. Queen (OKB-1) and installed on the German A4 / V-2. but it was less than half. The first test launch took place on April 18, 1953. Some difficulties arose with the pilot model's kerosene fuel and its leakage, the first version of the rocket, known in the USSR as the R-11 and 8K11, and in the west, the SS-1B "Scud-A" entered service in July 1955. This missile was classified as a weapon of the operational-tactical level.
The range of the R-11 rocket on the chassis of the IS-2 tank was 180 km, and the power of the atomic charge was 50 kT. The circular probable deviation (CEP) was equal to 3 km. In 1962, an improved version of this model was released, known in the West as the SS-1C Scud-V, and in the USSR as the R-17 (8K14) 9K72 Elbrus missile system. The R-17 had an improved guidance system, using an elementary inertial system with three gyroscopes. The rocket's fuel mixture was improved to include dimethyl hydrazine and red fuming nitric acid. To increase mobility, the system was installed on an eight-wheel base MAZ-543P. Apart from conventional means defeat, the missile warhead could be equipped with chemical and atomic. By 1970, the R-17 missile accounted for 75% of the 300 Scud installations in service.
silo missiles UR-100N UTTH
Later, the R-17M (9M77) system (SS-1D "Scud-S") appeared with a lightweight warhead of 600 kg, which is separated at the moment the engine is turned off, and a range of about 550 km. However, it was not clear whether this model was put into service. The SS-1E "Scud-D", designed in the late 80s, had an improved guidance system that included an active radar guidance station in the final section of the trajectory, a wide choice of warheads and a range of 700 km.
The R-11FM was developed as a weapon system for installation on submarines and has been in production since 1955. In September-October 1955, missile tests were carried out in the White Sea from the Project 611 submarine. This missile had a range of 150 km and was approved in 1959 for naval operations. The R-11 FM was not used in combat operations. In the USSR, the Scud-V and Scud-S systems were put into service at the level of the army and army group in brigades consisting of a headquarters division with three firing batteries each, three launchers, three reloading systems each, carrying one missile .
Scud-A and Scud-B were exported to Warsaw Pact countries, Egypt, Syria, Libya, Iraq and South Yemen, Libya. In 1986, in response to US attacks, Libya fired two Scud B missiles at US naval installations in Italy. However, the missiles did not hit the target. On January 17, 1991, Iraq fired Scud-B at Tel Aviv. Saddam Hussein used these missiles in response to the unfolding military campaign against the capture of Kuwait. Although the missiles were loaded with conventional weapons, the Israelis feared that Iraq, which had already used chemical weapon in the course of the war with Iran, does not use something even more terrible.
For the first time, Iraq used the Scud-B in the war with Iran for attacks on Tehran. In 1991, eight Scud missiles exploded in Israel during the first night of the Gulf War. In addition, on the first night, Iraq launched rocket attacks on Saudi Arabia. By the end of the war, 86 Iraqi Scud missiles had been fired (40 at Israel and 46 at Saudi Arabia). A small number of Iraqi Scud missiles were destroyed during the war, so they are still a potential weapon of mass destruction.
The performance characteristics of the rocket R-17 (8K14) ("Scad-V")
R-17 (8K14) ("Scud-V") photo
The famous Scud, a missile widely used in the world, was used in a number of local conflicts at the end of the 20th century.
The operational-tactical missile system 9K72 "Elbrus" with the 8K14 missile on long-term fuel components is designed to destroy manpower, command posts, airfields and other critical enemy targets.
It was created from 1958 to 1961 at SKB-385 (now the State Rocket Center named after academician V.P. Makeev), chief designer Viktor Makeev. March 24, 1962 adopted.
Initially, the 8K14 missile was placed on the 2P19 tracked chassis based on the ISU-152, structurally similar to the R-11M missile launchers, but subsequently all the complexes were transferred to the MAZ-543A wheeled chassis (9P117 launcher).
Rocket complex 8K14 (R-17) single-stage liquid, high-boiling fuel components: fuel TM-185 (special "rocket kerosene", which is a mixture of hydrocarbons close to turpentine) and oxidizer AK-27I (the so-called "melange": solution of nitrogen tetroxide in nitric acid).
The length of the rocket is 11.16 meters, the diameter is 0.88 meters, the weight of a fully fueled product is 5860 or 5862 kg (depending on the type of warhead). The range of the missile is from 50 to 300 km. Modification 8K14-1 (R-17 M) was interchangeable with 8K14 and did not differ in performance characteristics, all changes concerned the aggregate layout, which allows carrying heavier warheads.
The warhead of the rocket is inseparable, produced in several forms. In the usual equipment, it was a regular high-explosive fragmentation warhead 8F44 weighing 987 kg, equipped with an explosive TGAG-5 (TNT-RDX-aluminum mixture with a phlegmatizer).
The special (nuclear) equipment of the rocket provided for the installation of the 8F14 warhead (“product 269A”) weighing 989 kg and with a power of 10 kt, then the 9N33 family of warheads with charges of various capacities, including thermonuclear ones. There were also two versions of special warheads in chemical equipment. Since 1967, the rocket has been equipped with a 3N8 warhead with a mustard-lewisite mixture (withdrawn from service since the 1980s) and 8F44G "Fog-3" equipped with nerve-paralytic V-gases ("substance 33").
In the early 1980s, on the basis of 8K14, experiments were carried out to create high-precision ballistic missiles with a guidance system based on optical (Aerophone theme) and radar correlation seekers that used guidance compared to photographs or radar portraits of the terrain.
In the 1990s, the complex was gradually withdrawn from service, however, according to a number of reports, back in the late 2000s, part of the missiles were in long-term storage.
The Elbrus missile system was widely supplied abroad - not only to members of the Warsaw Pact, but also to the allies of the USSR in the Third World. Over the years, the R-17E (R-300) complex was received by Afghanistan, Bulgaria, Hungary, Vietnam, the GDR, Egypt, North Korea, Libya, Iraq, Iran, Poland, Romania, Syria, Czechoslovakia, etc. As a result, "scadas" (from NATO designation Scud) have become a key source of missile technology for the Third World.
First combat use complex took place in 1973, it was used by Egyptian troops against Israel during the "Doomsday War" in the fall of 1973. Further, Elbrus was used by Iraq against Iran during the 1980-1989 war. Elbrus also proved itself during the 1991 Gulf War and during the Second Chechen campaign in 1999-2001. Occasionally, the rocket was used during civil wars in Yemen and Afghanistan.
