he RT-2 is a three-stage missile with sequentially arranged stages and a single reentry vehicle. According to Western estimates, the missile was capable of delivering a 1200 lb reentry vehicle to a maximum operational range of 5500 nm with a CEP in the range of 0.7 to 1.0 nm. The three sustainer stages, using solid-propellant motors, were connected by trellised trusses. Four trellised aerodynamic stabilizers were used to stabilize the missile during the active trajectory leg. The flight control was implemented with the help of four split nozzles. With a nose cone of 500 kg it had a maximum range of 10,000-12,000 km, which was reduced to 4,000-5,000 km when employing a heavier nose cone of 1,400 kg. The guidance/control system incorporated a gyro-stabilized platform with floating gyros and pendulous accelerometers. Three variants of the SS-13 reentry vehicle have been identified. The Mod 1 variant had a ballistic coefficient of approximately 300 lb per sq ft and a CEP assessed in the West of about 1.0 nm. The Mod 2 has a ballistic coefficient of approximately 730 lb per sq ft and a CEP assessed at about 0.7 nm. Both had a yield in the range 0.6 to 1.5 MT, according to Western sources. The system was deployed in hardened and dispersed unmanned silos. Silo and launch control hardness was estimated by Western sources at 1300 psi overpressure. Because of the heavy weight of the missile it was transported in parts. The first stage was separated from the second and third stage. The assembly of a missile was directly carried out in the silo. The silo door was sealed and the ensuing special climate conditions in the silo guaranteed an extended storage of the solid-propellant.