UR-100N / SS-19 STILLETO  

Overview  

Specifications
Images
Sources and Resources

Once regarded by some as the "backbone" of the Soviet ICBM force, the fourth generation UR-100N / SS-19 intercontinental ballistic missile is a two-stage, tandem, storable liquid-propellant missile. The SS-19 is approxiamately 80 feet long and 8 1/2 feet in diameter. It was a competing design with the SS-17 Spanker, though in fact both were deployed to partially replace the SS-11 force.

The UR-100N is similar to the UR-100, but with an increased diameter and longer propellant tanks its launch weight was more than doubled and the throw-weight was increased over three-fold. The UR-100N uses asymmetrical dimethylhidrazine and nitrogen tetraoxide propellants. The first stage consists of four autonomous closed-cycle single-chambered rocket motors. The second stage has a closed-cycle single chambered sustainer and a four chambered open cycle control motor with four rotating nozzles. The guidance and control system of the SS-19 is identical to that of the SS-18, and permits remote monitoring of missile status while on alert, as well as automatic pre-launch preparation, remote missile targeting before launch and in-flight control of the missile via a flexible pitch control program. The UR-100N silos were constructed at the same sites as the UR-100U silos but were completely dismantled and rebuilt to increase the survivability of the new missiles. The UR-100N was launched in the hot mode through the thrust of the first stage sustainer engine.

The SS-19 has been deployed in three configurations.

  • SS-19 Mod-1 - Through the increase of throw-weight and reduction of the size of the warheads relative to the UR-100 the UR-100N carries six MIRV warheads with a yield of 550 KT each according to Russian sources [Western estimates suggested a yield of one- to two-megatons]. According to Western estimates the booster alone was limited to a range of 4900 nm but the total system, booster plus PBV, was assessed as being capable of delivering all six RVs to a maximum range of 5200 nm. Development was approved on 19 August 1970 and developed by V. N. Chelomey. The flight tests of the UR-100N were conducted at the Baikonur cosmodrome from 09 April 1973 through October 1975. The missile was initially deployed on 30 December 1975, though according to Western estimates it achieved an initial operational capability in 1974. The first regiment with UR-100N missiles was put on alert on 26 April 1975 and by the end of 1975 a total of 60 launchers were deployed. The missile employed an inertial guidance system that was is estimated by some Western sources to have an operational CEP of 0.3 nm in 1975 with a potential CEP of 0.25 nm by 1980. However, due to the hasty deployment of the UR-100N a major design flaw was overlooked. Training launches that took place after its deployment revealed a significant reduction of accuracy due to resonant oscillations of the missile. Subsequently all deployed missiles were modified to eliminate the problems.
  • SS-19 Mod-2 - Otherwise similar to the Mod-1, this variant carries a single warhead with a yield reported by Russian sources of between 2.5 and 5 MT. Between 1976 and 1978 the UR-100N reached its maximum operational inventory of 180 missiles, of which 60 carried a single warhead. Both of these SS-19 Mods were attributed "hard target kill" capabilities by the West.
  • SS-19 Mod-3 -The development of an improved version was authorized on 16 August 1976. The upgrades to the missile involved the development of improved engines and modification of the command system. The extent of protection from a nuclear strike at their silos was considerably improved. The flight-design tests of the improved version that received the designation UR-100NUTTH were conducted between 26 June 1979 and 26 October 1979. Its deployment began on 05 November 1979.
The first regiment with the UR-100NUTTH was put on alert on 06 November 1979. Between 1980-1982 UR-100N missiles with a single warhead (SS-19 Mod 2) were replaced by the UR-100NUTTH (SS-19 Mod 3). The replacement of all UR-100N missiles was completed in 1983. In 1984 the UR-100NUTTH reached its maximum operational inventory of 360 missiles. From 1987 on they were gradually replaced by new missiles. The silo-based version of the SS-24 replaced some SS-19s.

When the START-1 treaty was signed in 1991 the Soviet Union had a total of 300 UR-100NUTTH missile stationed in Russia and Ukraine. After the dissolution of the Soviet Union Ukraine claimed ownersip of the missiles located on its territory. In compliance with the START treaty provisions Ukraine is in charge of the dismantling the launchers for the SS-19 missiles. However, all nuclear warheads that were deployed in Ukraine were dismantled by Russia.

Some 170 launchers remain in Russian territory, of which 10 were deactivated but not dismantled. In December 1995 Strategic Rocket Forces Commander Colonel General Igor Sergeyev announced a policy under which the service life of the SS-19 would be extended from 10 years to 25 years. The missiles will remain on alert at least through 2005, and the missiles that were deployed in the early 1980s will serve beoynd this.

Following the ratification of the START-II treaty by the Duma, Russia is obliged to dismantle all ground-based ICBMs with multiple warheads. Under the treaty provisions a total of 105 of the UR-100NUTTH missiles can be retained provided they are downloaded to carry only one warhead instead of six.

Specifications     Return to Top
 

Mod-1

Mod-2

Mod-3

DIA

SS-19

SS-19

SS-19

NATO

Stiletto

Stiletto

Stiletto

Bilateral

RS-18A

RS-18A UTTKh

RS-18B

Service

UR-100N

UR-100N

UR-100NU

OKB/Industry

15A30

15A30

15A35

Design Bureau

OKB-52, KB Salyut,

Acad. V. N. Chelomey

OKB-52, KB Salyut,

Acad. V. N. Chelomey

OKB-52, KB Salyut,

Acad. V. N. Chelomey

Approved

8/19/1970

8/19/1970

8/16/1976

Years of R&D

1964-73

1964-1973

  

Engineering and

Testing

1973-75

1973-75

1977-79

First Flight Test

9/15/1972 failure & 12/28/1973 success

4/9/1973

10/26/1977

IOC

4/26/1975

1975

1979

Deployment Date

12/301975

12/30/1975

11/5/1979

Type of Warhead

MIRV

Single

MIRV

Warheads

6

1

6

Yield per Warhead (Mt)

0.5 0.55 0.750

2.5 - 5.0

0.5-0.75

Payload (t)

4.350

4.350

4.350

Total length (m)

24.0

24.0

24.3

Total length w/o

Warhead (m)

21.1

21.1

21.1

Missile Diameter (m)

2.50

2.50

2.50

Launch Weight (t)

103 - 105.6

105.6

103.4 - 105.6

Fuel Weight (t)

93.1

93.1

93.1

Range (km)

9,650

10,000

10,000

CEP (m)

(Russian Sources)

?

?

920

CEP (m)

(Western Sources)

350-550

250-400

220-380

Number of Stages

2

Canister length (m)

19.4

Canister length w/o

front meters (m)

  

Canister diameter (m)

2.9

Booster guidance system

Inertial


 

1st stage

2nd stage

3rd. Stage

Length (m)

17.2

2.8

  

Body diameter (m)

2.5

2.5

2.5

Fueled weight (t)

86.3

86.3

  

Dry weight (t)

      

Engine Designation

RD-0233 / RD-0234

RD-0235 (14/15D113)

N/A

Vernier Engine Designation

N/A

RD-0236 (15D114)

N/A

Bus Engine Designation Third Stage

N/A

N/A

RD-0237

Design Bureau Main Engines

OKB-154, Acad. S. A. Kosberg

OKB-154, Acad. S. A. Kosberg

N/A

Design Bureau Vernier Engine

N/A

OKB-154, Acad. S. A. Kosberg

N/A

Design Bureau Bus Engine Third Stage

N/A

N/A

OKB-154, Acad. S. A. Kosberg

Configuration

Cluster of four engines

One engine

N/A

Configuration Vernier Engine

N/A

Four vernier chambers

N/A

Configuration Bus engine Third Stage

N/A

N/A

Four chambers

Years of R & D

1969 1974

1969 - 1974

N/A

Years of R & D Vernier Engine

N/A

1969 - 1974

N/A

Years of R & D Bus Engine Third Stage

N/A

N/A

1969 - 1974

Propellants

Liquid

Liquid

Liquid

Fuel

UHMH

UDMH

UDMH

Oxidizer

Nitrogen Tetroxide

Nitrogen Tetroxide

Nitrogen Tetroxide

Burning time (sec.)

      

Main Engine Thrust Sea Level/Vacuum (Tonnes)

46.961/52.958 - 53.1

24.5 Vacuum

N/A

Verniers Thrust Sea Level/Vacuum (Tonnes)

N/A

1.6 Vacuum

N/A

Third Stage Bus Engine Thrust Vacuum (Tonnes)

N/A

N/A

0.5 Vacuum

Total Thrust Sea Level/Vacuum (Tonnes)

187.8442/207.8319

30.9 Vacuum

2.0 Vacuum

Main Engine Specific Impulse Sea Level/ Vacuum (sec.)

291 / 310

320 Vacuum

N/A

Vernier Engine Specific Impulse Sea Level/Vacuum (sec.)

N/A

293 Vacuum

N/A

Bus Third Stage Engine Specific Impulse Vacuum (sec.)

N/A

N/A

?


Basing Mode

Silo

Hardness

  

Launching Technique

Hot

Deployed boosters

  

Test Boosters

  

Warheads Deployed

  

Training Launchers

  

Space Booster Variant

Yes SL-X- ? , Rockot


Deployment Sites

START

Locale US-Designation

Khmel?Nitskiy

Derazhnaya

Kozel?sk

Kozelsk

Pervomaysk

Permovaysk

Tatishchevo

Tatishchevo

Images  Return to Top


SS-19/RS-18  in Launch Canister
SS-19/RS-18
Missile
SS-19/RS-18
Stage 1
 

SS-17/RS-16 and SS-19/RS-18 Emplacement Equipment

Sources and Resources     Return to Top