|Used by||Soviet Union|
|Blast yield||1.65Mt ("light") or 2.3Mt ("heavy") warheads|
|inertial, Control system by NII-885 of N.A.Pilyugin and M.S.Ryazanski. Gyroscopes by NII-944 of V.I.Kuznetsov.|
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. Control system for this rocket has been designed by NPO "Electropribor" (Kharkiv, Ukraine).
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. The initial stage of the two stage missile was a four-chambered closed cycle design developed by OKB-456 (later renamed to NPO Energomash). 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.
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 unfuelled 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.
- 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 No1 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.
- 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.