R-26

Ukrainian intercontinental ballistic missile. Two stage light ICBM developed 1960-1962, but cancelled so that Yangel could concentrate his efforts on the R-36. After project cancellation, a mock-up of this missile was shown in Moscow parades and misidentified for years by Western analysts as the 'SS-8'.

Development of the R-26 was begun by Yangel in accordance with a decree of 23 May 1960. This called for development of a silo-launched ICBM that could be stored for years as a sealed 'certified round' and then launched in minutes. The original decree optimistically called for flight trials to begin in December 1961, but by February 1962 the actual project had only reached the point of testing of an electrical mock-up of the missile. However by then Yangel's organization was wholly occupied with getting the R-16 into service after the disastrous explosion of 24 October 1961. In April 1962 a decree was issued for Yangel to begin development of the R-36 heavy ICBM, and the leadership felt that all of his organization's effort should be devoted to that project. Accordingly on 9 July 1962 all further work on the R-26 was stopped. LC-41A, which had been prepared for flight tests of the rocket, was converted to use as an alternate R-16 pad.

As a cancelled project the artifacts of the rather advanced development program proved useful. A mock-up of this missile was shown in a Moscow parade on 7 November 1964 and misidentified for years by Western analysts as the 'SS-8 Sasin' (which was actually Korolev's R-9). A sectioned version of the missile was put on display at Orevo for instructional purposes. Models were displayed at the museum in Baikonur, but no completed flight-test missiles had been delivered there yet at the time of cancellation..

Maximum range: 12,000 km (7,000 mi). Number Standard Warheads: 1. Warhead yield: 3,000 KT. CEP: 2.00 km (1.20 mi). Boost Propulsion: Nitric acid/UDMH. Cruise engine: U102-000.

Stage Data - R-26

• Stage 1. 1 x R-26 Stage 1. Gross Mass: 60,300 kg (132,900 lb). Empty Mass: 3,000 kg (6,600 lb). Thrust (vac): 1,451.000 kN (326,197 lbf). Isp: 310 sec. Burn time: 160 sec. Isp(sl): 251 sec. Diameter: 3.00 m (9.80 ft). Span: 15.00 m (49.00 ft). Propellants: Nitric acid/UDMH. No Engines: 1. Engine: RD-224. Other designations: 8K66. Status: Out of Production. Comments: Orevo has sectioned hardware. Tsniimash has 1:10 structural simulation model. All figures accurate except empty mass estimated. Source: Placard, TsNIIMASH, Orevo.

• Stage 2. 1 x R-26 Stage 2. Gross Mass: 25,200 kg (55,500 lb). Empty Mass: 2,500 kg (5,500 lb). Thrust (vac): 428.060 kN (96,232 lbf). Isp: 308 sec. Burn time: 160 sec. Isp(sl): 252 sec. Diameter: 2.40 m (7.80 ft). Span: 8.73 m (28.64 ft). Propellants: Nitric acid/UDMH. No Engines: 1. Engine: U102-000. Other designations: 8K66. Status: Out of Production. Comments: Orevo has sectioned hardware. Tsniimash has 1:10 structural simulation model. All figures accurate except empty mass estimated. Source: Placard, TsNIIMASH, Orevo.