Tuesday, 25 October 2016

R-36M / SS-18 SATAN Intercontinental ballistic missile


The R-36 (NATO designation SS-9 Scarp) was the first model of the whole R-36 family of Soviet intercontinental ballistic missiles. First cold-launch tests were conducted in January 1971. This version, called Mod 1, was able to carry single nuclear warhead with blast yield of 18-25 MT, and it had a range of 11 200 km.
Later the R-36 missile evolved into the R-36M (SS-18 Satan), capable of carrying a MIRV payload of 10 warheads. Each with 550-750 kT yield. It could also carry a single warhead of up to 20 MT. Development of this missile began in 1969. The first test launch was made in 1973. First batch of 56 missiles were deployed in 1977, but were later replaced by more modern Mod 3 and Mod 4 variants.
All variants of the Satan are silo-launched. Silos are located in dispersed locations. The silo launcher and command point are hardened against a nuclear explosion. Source military-today

Image: Kosmotras/Spaceflight101
The R-36m / SS-18 intercontinental ballistic missile is a large, two-stage, tandem, storable liquid-propellant inertial guided missile developed to replace the SS-9 ICBM. Housed in hard silos, the highly accurate fourth generation SS-18 ICBM is larger than the Peacekeeper, the most modern deployed US ICBM. The SS-18 opened a "window of vulnerability" of Minuteman silos (at 300 psi) by 1975, so that some analysts aregued that few Minuteman could be expected to survive a Soviet attack by 1980. The "window of vulnerability" of U.S. land based strategic missiles opened on schedule, and became one of the major issues in U.S. strategic debates in the late 1970s and early 1980s.

Image - phys.org

The R-36M (15A14) was a two-stage missile capable of carrying several different warheads. The basic design is similar to the R-36 missile modified to include advanced technologies and more powerful engines. This missile, using dinitrogen tetroxide (N2O4) and heptyl (a UDMH [unsymmetrical dimethyl hydrazine] compound) has a first stage powered by a 460-ton-thrust motor with four combustion chambers, and the second by a single-chamber 77-ton-thrust motor. The first stage uses four closed-cycle single chambered rocket motors. 


The second stage was equipped with a closed-cycle single chambered sustainer motor and an open-cycle four chambered control motor. The second stage sustainer is built into the fuel tank's toroidal cavity. The flight control of the first stage was conducted through gimbaled sustainers. The sustainers used asymmetrical dimethylhydrazine and nitrogen tetraoxide. The missile was equipped with an autonomous inertial command structure and an onboard digital computer.

The R-36M used a gas-dynamic method for the first and second stages whereby special ports are opened through which the propellant tanks are pressurized. This obviated the need for the use of pressurant gases from tanks and the so-called chemical tanks pressurization (by injecting small amounts of fuel in the oxidizer tank and oxidizer into the fuel tank). The improved design and more effective engines allowed an increase in the total liftoff weight from 183 tons to 209.6 ton and the throw weight from 5.8 tons to 8.8 tons, while maintaining the overall dimensions of its predecessor missile.

The SS-18 was deployed in modified SS-9 silos, and employed a cold-launch technique with the missile being ejected from the silo prior to main engine ignition. The rocket was placed in a transport-launch canister made of fiberglass composites. The container was placed into an adapted R-36 silo. The specially hardened silo was 39 meters deep and had a diameter of 5.9 m. Prior to main engine ignition the missile was ejected from the container with the help of a solid-propellant gas generator located in the lower unit of the transport-launch canister. According to Western estimates, the SS-18 was deployed in a silo with a hardness of at least 4,000 psi (281 kg/sq. cm; 287 bar), and possibly as high as 6,000 psi (422 kg/sq. cm; 430 bar).

The development of the two stage heavy liquid-propellant ICBM R-36M intended to replace the R-36 SS-9 Scarp was accepted on 02 September 1969. The preliminary design was completed in December 1969 by the design bureau was KB Yuzhnoye. The system was designed by the M. K. Yangel OKB Yuzhnoye at Dnepropetrovsk (Ukraine) during 1966-1972, with testing beginning in November 1972. It was deployed in January 1975, and integrated with the weapons arsenal in December 1975.


There are six variants that have been deployed, while others were tested but not deployed:
  • SS-18 Mod 1 - R-36M The SS-18 Mod 1 carried a single large reentry vehicle, with a warhead yield of 18 to 25 MT, a distance of about 6,000 nm. In January 1971 pop-up tests, began during which the mortar launch was perfected. The actual flight tests for the single-RV Mod-1 began on 21 February 1973, though some sources suggest that testing began in October 1972. The testing phase of the R-36M with various different types of warheads was finished in October 1975 and on 30 December 1975 deployment began [though some Western sources suggest that an initial operational capability was reached in early 1975]. A total of 56 were deployed by 1977, though all were replaced by Mod 3 or Mod 4 missiles by 1984. These high-yield weapons were assessed in the West as possibly developed to attack American Minuteman ICBM launch control centers.
  • SS-18 Mod 2 - R-36M The SS-18 Mod 2 included a post-boost vehicle and up to eight reentry vehicles, each with a warhead yield estimated at between 0.5 to 1.5 MT, with a range capability of about 5,500 nm. The MIRVs were placed in pairs, and a post boost vehicle with a command structure and a propulsion system were contained in the nose cone of the R-36M. The flight tests of the MIRVed Mod-2 began in September 1973 [though some Western sources suggest that the initial flight test of the Mod 2 MIRV version occurred in August 1973], with IOC in 1975. Approximately 132 were deployed by 1978, but the post-boost vehicle design was seriously flawed, and the Mod 2 missiles were all replaced by the Mod 4 variant by 1983.
  • SS-18 Mod 2x - R-36M Between July 1978 and August 1980 a MIRVed missile with an improved nose cone was tested but not deployed. The fact of the existence of this system is reported by Russian sources, but not attested by unclassified Western literature.
  • SS-18 Mod 3 - R-36UTTh The SS-18 Mod 3 carried a single large reentry vehicle that was an improved version of the SS-18 Mod-1. On 16 August 1976, a few months after the R-36M entered service, the development of an improved modification of the R-36M (15A14) and MR UR-100 (15A15) was approved. This missile subsequently received the designation R-36M UTTh (15A18) and was developed by KB Yuzhnoye (OKB-586) through December 1976. Its increasing accuracy made it possible to reduce the yield of the warheads. The R-36M UTTh was capable of carrying two different nose cones. The version with a divided nose cone [Mod-4] allowed an increase the numbers of warheads from 8 up to 10 and the single-RV version [Mod-3] had a maximum range of up to 16,000 km. The flight-design tests of the R-36M UTTh began on 31 October 1977. On 29 November 1979 deployment of the SS-18 Mod-3 with a single reentry vehicle carrying a warhead with a yield of 24-25 MT began. The P-36MUTTh was introduced into the inventory on 17 December 1979. A total of 24 were deployed in 1977, and all were replaced by the Mod 4 variant by 1984.
  • SS-18 Mod 4 - R-36UTTh The SS-18 Mod 4 carries at least 10 MIRVs and was probably designed to attack and destroy ICBMs and other hardened targets in the US. According to some Western estimates, evidence suggested that the Mod 4 may be capable of carrying as many as 14 RVs [this may reflect observation of the deployment of countermeasures intended to overcome a ballistic missile defense, or to confuse American attack characterization systems]. In November 1979 the flight tests of the MIRVed missile were completed. The first three regiments were put on alert on 18 September 1979. During 1980 a total of 120 SS-18 Mod 4 missiles were deployed, replacing the last remaining R-36 missiles. In 1982-1983 the remaining R-36M missiles were also replaced with the new R-36M UTTh and the total number of deployed missiles reached a maximum operational launcher reached 308, ceiling established in the SALT-1 treaty. The SS-18 Mod 4 force had the estimated capability to destroy 65 to 80 percent of US ICBM silos using two nuclear warheads against each. Even after this type of attack, it was estimated that more than 1,000 SS-18 warheads would be available for further strikes against targets in the US. After 1988 the SS-18 Mod 4s were partially replaced by the new R-36M2 "Voivode".
  • SS-18 Mod 5 - R-36M2 "Voivode" The newer, more accurate version (the SS-18 Mod 5) placed in converted silos allowed the SS-18 to remain the bulwark of the SRF's hard-target-kill capability. The Mod 5 carries 10 MIRVs, each having a higher yield than the Mod 4 warheads. The Mod-5 warheads have nearly twice the yield of the Mod-4 (approximately 750 kt to 1 megaton) according to Western estimates, though Russian sources suggest a yield of 550-750 Kt each. The increase in the Mod 5's warhead yield, along with improved accuracy, would, under the START treaty, help allow the Russians to maintain their hard-target-kill wartime requirements even with the 50 percent cut in heavy ICBMs the START agreement required. The technical proposals to build a modernized heavy ICBM were made in June 1979. The missile subsequently received the designation R-36M2 "Voivode" and the industrial index number 15A18M. The design of the R-36 M2 "Voivode" was completed in June 1982. The R-36M2 disposed of a series of new engineering features. The engine of the second stage is completely built in the fuel tank (earlier this was only used on SLBMs) and the design of the transport-launching canister was altered. Unlike the R-36M, the 10 warheads on the post-boost vehicle are located on a special frame in two circles. The flight tests of the R-36M2 equipped with 10 MIRVs began in March 1986 and were completed in March 1988. The first regiment with these missiles was put on alert on 30 July 1988 and was deployed on 11 August 1988.
  • SS-18 Mod 6 - R-36M2 "Voivode" The flight tests of a the R-36M2 missile (Mod-6) carrying a single warhead with a yield of 20 MT were completed in September 1989 and deployment began in August 1991.

Specifications

Mod
Mod-1
Mod-2
Mod-3
Mod-4
Mod-5
Mod-6
DIA
SS-18
SS-18
SS-18
SS-18
SS-18
SS-18
NATO
Satan
Satan
Satan
Satan
Satan
Satan
Bilateral
RS-20A
RS-20A
RS-20A
RS-20B
RS-20V
RS-20V
Service
R-36M
R-36M
R-36M
UTTkh
R-36MU
UTTkh
R-36M2
R-36M2
OKB/Industry
15A14
15A14
15A14
15A18
15A18M
15A18M
Design
Bureau
OKB-586
Acad. V. F. Utkin
OKB-586 Acad. V. F. Utkin
OKB-586
Acad. V. F. Utkin
OKB-586
Acad. V. F. Utkin
OKB-586 Acad. V. F. Utkin
OKB-586 Acad. V. F. Utkin
Approved
9/2/1969
9/2/1969
9/2/1969
8/16/1977
8/9/83
6/1979 ?12/17/
1980 ?
Years of R&D
1969-1973
1969-1973

12/ 76 - 78
1983-1988
1979-1982
Engineering and Testing
1973-1974
1973-1975
1978-1980
1977-1979
1986-88
1986-1990
First Flight Test
1 / / 72 1St. failure
2/21/1973 success 1 & another derivation 11-29-79
9/ /73,
08/ /73 & another derivation
07/ /78
7/ /1978
7/31/1977
or 10-31-1977
3/21/86
two failures in the flight test program
1986
IOC
12 /25 / 1974
1975
1980
9/1979 ? 11-27-1979?
12/1988
1990
Deployment Date
12/30/
1975
12/30/
1975 or 11/20/78
11/29/
1979
12/17/
1979, or 1980?
12/1988
9/1991
Type of
Warhead
Single
MIRV
Single
MIRV
MIRV
Single
Warheads
1
8
1
10
10
1
Yield (Mt)
Russian sources
18-20
0.5-1.3
24-25
0.55
0.55-0.75
20
Yield (Mt)
Western sources
18-25
0.6-1.5
18-25
0.75-1.0
Payload (t)
7.2
7.2 - 8.8
7.2 - 8.8
8.8
8.8
8.8
Total length (m)
33.6
33.6
33.6
34.3
37.25
36.3
Total length w/o warhead (m)
28.5
28.5
28.5
28.5 -29.25
29.25
29.25
Missile Diameter (m)
3.0
3.0
3.0
3.0
3.0
3.0
Launch Weight (t)
209.6 -210
209.6 -210
209.6 -210
211.1
211.1
211.1
Fuel Weight (t)
188
188
188
188
188
188
Range (km)
11200
9250-10200
16.000
16000
11500
11000
15,000
16000
CEP (m)
Russian Sources
1000
1000
1000
920
500
500
CEP (m) Western Sources
400-550
400-500
350
220-320
250
?250

Number of Stages
2
Canister length (m)
27.9
Canister diameter (m)
3.5
Booster guidance system
Inertial, autonomous


1st stage
2nd stage
Length (m)
22.3
7.0
Body diameter (m)
3.0
3.0
Fueled weight (t)

Total 161.5
Dry weight (t)

Total 48.1 ? 48.5
Engine Designation
RD-263 x 4 = RD-264 (11D119) for the
R-36M
RD-0228 = RD-0229 one main engine and RD-0230 four verniers for the R-36M
Engine Designation
RD-273 / RD-274 for the R-36MU
RD-0230 verniers for the R-36M
Engine Designation
N/A
RD-0255 = RD-0256 one main engine & RD-0257 four verniers for the R-36M2.
Design Bureau
Acad. V. P. Glushko (OKB-456)
Acad. S. A. Kosberg
(OKB-154)
Configuration
Four RD-263?s Engines = RD-264
1 Main Engine + 4 Verniers
Years Of R & D
1969-1973 = RD-263 x 4=RD-264
1967-1975 = RD-0228 / RD-0229
Years Of R & D
1975-1980 = RD-273
1967-1975 = RD-0230
Years Of R & D

1983-1989 = RD-0255
1983-1987 = RD-0256
1983-1987 = RD-0257
Propellants
Liquid Storable
Liquid Storable
Fuel
UDMH
UDMH
Oxidizer
Nitrogen Tetraoxide
Nitrogen Tetraoxide
Burn Time (sec.)


Main Engines Thrust Sea Level/Vacuum (Tonnes)
424 / 450-461
77
Verniers Engine Thrust Sea Level/Vacuum (Tonnes)
N/A
?
Main Engines Specific Impulse Sea Level/ Vacuum (sec.)
293 / 312-318




MIRV Bus Third Stage Engine Designation for the R-36M2

RD-869
Design Bureau (Bus)

Yuzhnoy SKB
Years Of R & D (Bus)

1983-1985
Propellants (Bus)

Liquid Storable
Fuel (Bus)

UDMH
Oxidizer (Bus)

Nitrogen Tetraoxide
Thrust Vacuum (Tonnes)

2.087- 0.875
Engines Specific Impulse (sec.)

313 ? 302.3
Burn Time (sec.)

700

Basing Mode
Silo
Hardness

Launching Technique
Cold and Solid motor
Deployed boosters

Test Boosters

Warheads Deployed

Training Launchers

Space Booster Variant
Yes- SL-21?/Dnipr SS-18 derivation
Deployment Sites
START
Locale US-Designation
Aleysk in Altai (30)
Aleysk
Derzhavinsk near Akmolinsk (52)
Imeni Gastello
Dombarovsky-3 near Orenbourg (64)
Dombarovskiy
Kartaly-6 near Chelyabinsk (46)
Kartaly
Uzhur-4 near Krasnoyarsk (64)
Uzhur
Zhangiz-Tobe near Seminpalatinsk (52)
Zhangiz Tobe

Source fas.org