R-9 Desna

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R-9
SS- 8 Sasin.gif
Type ICBM
Service history
In service 1964–1976
Used by Soviet Union
Production history
Manufacturer OKB-1
Specifications
Weight 80.4 tonnes
Length 24.19 m
Diameter 2.68 m
Warhead 1
Blast yield 1.65Mt ("light") or 2.3Mt ("heavy") warheads

Engine Two-stage liquid fuel (kerosene + LOX)
  1. first stage engine RD-111 (8D716) by OKB-456 of V.P.Glushko.
  2. second stage engine RD-461 RO-9 (8D715) by OKB-154 of S.A.Kosberg
Operational
range
16,000 km [1]
Guidance
system
inertial, Control system by NII-885 of N.A.Pilyugin and M.S.Ryazanski. Gyroscopes by NII-944 of V.I.Kuznetsov.
R-9 ICBM and T-34 tank, on display at the Central Armed Forces Museum (Russia)

The R-9 (NATO reporting name: SS-8 Sasin) was a two-stage ICBM of the Soviet Union, in service from 1964 to 1976.

History

Designed in 1959 and first tested in 1961, the R-9 was a great improvement over previous Soviet missile designs. The missile, capable of delivering a 3,500 lb (1600 kg) payload about 6,000 nautical miles (11,000 km) to an accuracy of 1 nautical mile (2 km), was not only very accurate, but was also far more tactically useful to the Soviet Union. Previous Soviet designs, fuelled with cryogenic LOX and kerosene, commonly took hours to fuel and launch. The R-9, on the other hand, could be launched 20 minutes from the time a launch order was given. NPO "Electropribor" (Kharkiv, Ukraine) designed the missile's control system.[2]

First put into active service in 1964, the R-9 carried a 1.65 to 5 Mt warhead. Though the last Soviet missile to use cryogenic propellant, this design is one of the most widely deployed ICBMs to use cryogenic fuel. OKB-456 (later renamed to NPO Energomash) developed the initial stage of the two-stage missile, a four-chambered closed cycle design. The second stage, connected by trusses to the first stage (much like the modern Soyuz rocket) was also four-chambered, but utilized open combustion chambers more suited to very high altitudes. This rocket engine was a product of the OKB-154 design team. Guidance of the warhead, like most ICBMs before and after it, was totally inertial save the final ten seconds before detonation of the warhead, which was controlled by a radio-altimeter correction system.

Deployment

The initial design called for a mobile surface-launched system, but a changing cold war situation[further explanation needed] saw a silo-based R-9 developed in tandem with the ground-based system. The ground-based system, however, would never achieve the hoped-for mobility of the initial design parameters. In total, three launch sites were constructed, but only two were used. "Desna-V", the silo launch area, consisted of three underground silos with the ability to launch the R-9 within 20 minutes, and the ability to store the missile in an unfueled ready condition for one year. "Valley", the first of two above-ground launch sites, was mostly automated and could fire the R-9 within 20 minutes as well, and repeat the process within two and a half hours. The final launch site, "Desna-N", was also an above-ground site, but was never stocked with R-9s as the site was not automated and needed at least two hours to launch a single missile.

In 1971 the above-ground R-9 launch sites were decommissioned, and by 1976 all R-9 missiles had been decommissioned.

NATO reporting name

SS-8 Sasin is a NATO reporting name that was mistakenly applied to two different Soviet missile systems. The designation was accidentally applied to the R-26 when an example of that missile was revealed in a parade. However, the R-26 program had already been cancelled and no new designation was given by NATO for the R-26 once the error was discovered.

1963 fire

On October 24, 1963, an R-9 missile was being prepared for launch in a silo from Site 70 at Baikonur Cosmodrome. The 11-man launch crew did not realize that an oxygen leak from the missile's fuel system had raised the partial oxygen pressure to 32% (the maximum allowed was 21%). The crew was descending to the eighth level in a lift when a spark from an electrical panel started a fire in the nearly pure oxygen atmosphere, killing seven and destroying the silo. The disaster occurred exactly three years after the Nedelin disaster. October 24 became known as Baikonur's "Black Day", and to this day no launches are attempted on that date.

Data

  • Fuel: kerosene + oxygen.
  • Control system by NII-885 of N.A.Pilyugin and M.S.Ryazanski.
  • Gyroscopes by NII-944 of V.I.Kuznetsov.
  • Launcher by GSKB "Spetsmash" of V.P.Barmin.
  • First stage engine RD-111 (8D716) by OKB-456 of V.P.Glushko.
  • Second stage engine RO-9 (8D715) by OKB-154 of S.A.Kosberg.
  • 1.65Mt ("light") and 2.3Mt ("heavy") warheads.
  • Tested at "ground No 51" at NIIP-5 (Baikonur/Tura-Tam) until crash in October 1962.
  • Serial production at facility No. 1 in Kuibyshev.
  • Deployed 2 regiments of ground based missiles at Kozelsk, 1 regiment of ground based missiles at Plesetsk, 1 regiment of underground silo missiles at Kozelsk.

Operators

 Soviet Union
The Strategic Rocket Forces were the only operator of the R-9.

External links

  • R-9
  • R-9A /SS-8 Sasin Czech - More photos
  • The SS-8 Controversy Discusses the CIA's bewilderment about the new missile, with one camp interpreting it as a 100 megaton weapon, and other analysts interpreting it as a much smaller missile.

Footnotes

  1. ^ http://missilethreat.com/missiles/r-9-ss-8/?country=russia#russia
  2. ^ Krivonosov, Khartron: Computers for rocket guidance systems
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