R-36 (missile)

R-36; NATO Reporting name: SS-18 Satan
Senator Richard Lugar inspects an SS-18 ICBM being readied for decommission under the Nunn-Lugar Program

The R-36 (Template:Lang-ru) is a family of intercontinental ballistic missile and space launch vehicle designs created by the Soviet Union during the Cold War. The original R-36 was produced under the Soviet industry designation 8K67 and was given the NATO reporting name SS-9 Scarp. The modern version, the R-36M was produced under the GRAU designations 15A14 and 15A18 and was given the NATO reporting name SS-18 Satan; this missile gave the Soviet Union first-strike parity with the United States.

Description

The R-36 is a two stage rocket powered by storable liquid propellant (a bipropellant, with UDMH as fuel, nitrogen tetroxide as oxidizer) and carrying one of four different warheads developed for the missile. The Mod 1 and Mod 2 were single nuclear re-entry vehicles of 18 and 25 Mt of TNT yield respectively. The Mod 4 was a three-warhead MIRV payload, while the Mod 3 was a proposal for a FOBS which was not adopted.

The R-36P was developed to carry the Mod 4 warhead, while the R-36O was the launch vehicle for the Mod 3 FOBS.

R-36 and R-36P missiles were hot launched from their silos.

The R-36M is similar to the R-36 in design, but has the capacity to mount a single warhead of up to 20 Mt of TNT in yield, or a MIRV payload of up to 10 warheads, each with a 550-750 kt yield, throw weight of the missile is 8800 kg. This makes the Soviet R-36 the world's heaviest ICBM; for comparison, the heaviest U.S. MIRV is able to carry 10 warheads only 330 kt each, with a throw weight of 4000 kg. The missile has two stages. The first is a 460,000 kgf (4.5 MN) thrust motor with four combustion chambers and nozzles. The second stage is a single-chamber 77,000 kgf (755 kN) thrust motor.

All R-36 variants were designed to be launched from silos in dispersed and hardened locations. The R-36M is placed into its 39 m deep silo in a tubular storage/launch container. Upon launch the missile is shot out of the tube, mortar-fashion, by a piston, driven by the expansion of gases from a slow-burning black powder charge inside the piston. The missile's main engine is ignited tens of metres above the ground, preventing any damage to the internal equipment of the silo itself from the rocket engine's fiery efflux. This “cold start” enables quick removal of the empty launch tube from the silo, reloading a second missile in its container, and thus a second launch before the anticipated retaliatory strike arrives. Thanks to this second salvo capability, the system can launch twice the number of own missiles before the opposing counter-silo warheads can arrive at the launch site of the R-36M.

Development

Development of the R-36 was begun by OKB-586 (Yuzhnoye) in Dnepropetrovsk, Ukraine) in 1962, and built upon the work of the R-16 program. The Chief Designer was Mikhail Yangel. Initial development was of light, heavy, and orbital versions, with flight testing from 1962 through 1966, at which time initial operational capability was achieved. News of the development of the orbital version caused alarm in the West with the possibility that the Soviets would be able to launch large number of nuclear weapons into orbit where there was no capability to intercept them. The prospect of orbital nuclear weapons led both sides to agree a treaty banning the use of weapons of mass destruction in space.

In 1970, development of a fourth version, capable of delivering multiple warheads, was developed, and test flown the next year.

Further improvement of the R-36 led to the beginning of the design of the R-36M in 1969 with the probable mission of providing a first-strike capability to allow the destruction of United States LGM-30 Minuteman silos and launch controls before they could retaliate; this according to sources in the west, the Soviet Union and Russia Federation have never ascribed the weapon a particular role in their arsenal. The initial design of the R-36M called for a single massive 12-Mt warhead to be delivered over a range of 10,600 km. The missile was first tested in 1973 but this test ended in failure. After several delays the R-36M was deployed in December of 1975. This “Mod-1” design was delivered with a single 18–20 Mt warhead and a range of just over 11,000 km. This new version was given a new identity by NATO: SS-18 Satan.

The SS-18 has gone through six separate modifications, with the first modification (Mod-1) being phased out by 1984. The final modification (Mod-6) designated R-36M-2 “Voevoda” was deployed in August of 1988. This missile could deliver the same 18–20-Mt warhead 16,000 km. Modifications prior to Mod-6 mainly introduced MIRV (Multiple independent reentry vehicles) warheads. These missiles (Mods-2, 4, and 5) surpassed their western counterpart the US LG-118A Peacekeeper in terms of megatons delivered, range, and survivability, but were inferior in terms of accuracy (CEP).

Multiple warheads

Missiles of the R-36M/SS-18 family have never been deployed with more than ten warheads. But given their large throw-weight (8.8 tonnes as specified in START), they have the capacity to carry considerably more than that. Among the projects that the Soviet Union considered in the mid-1970s was that of a 15A17 missile—a follow-on to the R-36MUTTH (15A18). The missile would have had an even greater throw-weight—9.5 tonnes—and would be able to carry a very large number of warheads. Five different versions of the missile were considered. Three of these versions would carry regular warheads – 38x 250 kt yield, 24x 500 kt yield, or 15-17x 1 Mt yield. Two modifications were supposed to carry guided warheads (“upravlyaemaya golovnaya chast”) – 28x 250 kt or 19x 500 kt. However, none of these upgraded models were ever developed. The SALT II Treaty, signed in 1979, prohibited increasing the number of warheads ICBMs could carry. Equally, from a strategic point of view, concentrating so many warheads on silo-based missiles was not seen as desirable, since it would have made a large proportion of the USSR's warheads vulnerable to a counterforce strike.

The operational deployment of the R36M/SS-18 consisted of the R-36MUTTH, which carried ten 500kt warheads, and its follow-on, the R-36M2 (15A18M), which carried ten 800 kt warheads (Single-warhead versions with either 8.3 Mt or 20 Mt warhead also existed at some point). To partially circumvent the treaty, the missile, utilizing the capacity unused due to 10 warhead limitation, was equipped with 40 heavy decoys. These decoys would appear as warheads to any defensive system, making each missile as hard to intercept as 50 single-warhead, rendering potential ABM systems ineffective.

Deployment

At full deployment, before the fall of the Soviet Union in 1991, 308 R-36M launch silos were operational. After the breakup of the USSR, 204 of these were located on the territory of the Russian Federation and 104 on the territory of newly independent Kazakhstan. In the next few years Russia reduced the number of R-36M launch silos to 154 to conform with the START I treaty. The missiles in Kazakhstan were all deactivated by 1995. The subsequent START II treaty was to eliminate all R-36M missiles but it did not enter into force and the missiles remained on duty.

R-36orb

Entered service	1968
Range	Unlimited for targets below its orbital plane
Starting weight, tonnes	181.3
Warhead mass, kg	3648
Mass of missile defense countermeasures, kg	238
Length, metres	32.65
Diameter	3
Number of warheads	One
Yield	2.3 Mt
Type of control system	Inertial
Launch platform	Missile silo

The development of the Р-36 missile complex for use with the 8К69 fractional-orbit missile began on April 16th, 1962. Such a missile provides some advantages over a conventional ICBM. The range is limited only by the parameters of the orbit that the re-entry vehicle has been placed into, and the re-entry vehicle may come from either direction, compelling the enemy to build considerably more expensive anti-missile systems. Due to the possibility of placing the warhead in orbit and keeping it there for some time, it is possible to reduce the time required to strike to just a few minutes. It is also very much more difficult to predict where the warhead will land, since while the re-entry vehicle is on orbit, it is a very small object with few distinguishing marks and is hard to detect; moreover, since the warhead can be commanded to land anywhere along the orbit's ground track, even detecting the warhead on orbit does not allow accurate prediction of its intended target.

The structure and design of the fractional-orbit bombardment system were similar to a conventional P-36 ICBM system. A two-stage rocket was equipped by the liquid rocket engines using storable propellants. The silo launcher and command point were hardened against a nuclear explosion.

The basic difference from a conventional ICBM consists of the design of the re-entry vehicle, which is fitted with a de-orbit engine. Conventional ICBMs do not need to brake to leave orbit as their trajectory takes them to the surface of the earth anyway.

The Control system, orientations and stabilization OGCH — independent inertial. It(she) is added radiovysotomerom which supervises height of an orbit twice — in the beginning of an orbital site and before submission of a brake impulse. The brake step is intended for maintenance of descent(release) OGCH from an orbit. It(she) is equipped by own impellent installation, the automatic device of stabilization and the automatic device of management of the range, giving out a command(team) on deenergizing TDU.

During летно-design tests 19 rockets have been tested, from them 4 start-up were avarijnmi. In the seventeenth start-up rescue of a head part by means of parachute system has been carried out. Letnye tests of a rocket have been completed on May, 20th, 1968, and the rocket complex on November, 19th 1968г has been accepted on arms. The first and unique shelfs with 18 launchers for orbital rockets 8К69 has taken up fighting watch on August, 25th 1969г.

Orbital rockets 8К69 have been removed(have been taken off) from fighting watch in January, 1983 in connection with the conclusion of the Contract about restriction of strategic armaments (ОСВ-2). In this contract restriction on accommodation of the nuclear weapon in space has been entered.

In the further on the basis of a rocket 8К69 the family raketo-carriers "Cyclones" has been created.

Elimination

In the last decade Russian armed forces have been steadily reducing the number of R-36M missiles in service, withdrawing those that age past their designed operational lifetime. About 40 missiles of the most modern variant R-36M2 (or RS-20V) will remain in service until 2020 and will be then replaced by newer MIRV version of Topol-M.

Derivatives

Several remaining SS-18 missiles have been modified for surface launch and now carry lightweight satellites to low earth orbit, including many foreign payloads.

Ukraine’s Yuzhnoe Design Bureau continues to manufacture a launch vehicle based on the SS-18, named Dnepr.

Operators

• Soviet Union and Russia: The Strategic Rocket Forces have been the only operator of the R-36.

See also

• List of missiles
• List of rockets
• Strategic Rocket Forces

References

• Podvig, Pavel. (2001) Russian Strategic Nuclear Forces. Cambridge, MA: The MIT Press.

External links

• Russia's nuclear forces - 2006
• Yuzhnoe Design Bureau - English-language home page
• Russian strategic nuclear forces - webpage
• Federation of American Scientists