R-36-O Media Gallery

The R-36-O was the only orbiting military nuclear weapon ever deployed, although in order to remain legal under international treaties it was a 'fractional orbital' weapon. Although American infrared early warning satellites invalidated the 'surprise attack' component of the concept, 18 missiles were operational from 1969 to 1983.

The Global Rocket 1 (GR-1) requirement of 1961 called for a system to place a large nuclear warhead equipped with a deorbit rocket stage into a low earth orbit of 150 km altitude. The warhead could approach the United States from any direction, below missile tracking radar, so little warning was available. Not only could such a missile hit any point on earth, but the enemy would also be uncertain when it would be deorbited onto target. The disadvantages were greater complexity, lower accuracy, and the need to use a lighter warhead in comparison to an ICBM. Furthermore American development and deployment of infrared early-warning satellites in the 1970's invalidated the warning advantage.

Chelomei proposed his UR-200 for the requirement, while Yangel offered the R-36, and Korolev the 8K713. An official decree authorised development to begin in April 1962. Yangel completed his draft project in December 1962 and began flight tests of the basic R-36 ICBM in 1963. Development problems with Korolev's rocket resulted in continual delays, resulting in its cancellation in 1964. Following Khrushchev’s ouster from power in October 1964, Chelomei’s UR-200 project was reviewed and cancelled as well. This left Yangel’s R-36 for the mission.

Flight trials of the system began on 16 October 1965 from silos at LC-160 and LC-162 at Baikonur. Since orbiting of nuclear weapons was a violation of international treaty, the Soviet Union conducted all tests on a 'fractional orbit' basis - i.e. the test warheads were deorbited after less than one orbit of the earth. The launches were however logged and tracked as satellites by international treaty. There were four launches in 1966 and 10 in 1967. The United States only publicly noted the probable FOBS mission of the tests on 3 November 1967. The system was formally accepted for military service on 19 November 1968. A military regiment to operate the missiles was formed in August 1971. The system was in service at 18 silos at Baikonur from 25 August 1969 to January 1983. Under SALT-2 12 of these silos were demolished, the remaining six being retained for launch of R-36M's converted to orbital launch vehicle use. In common with other R-36 versions, the missile had a 7.5 year guaranteed fuelled storage life and a five minute reaction time.

The 8F021 orbiting warhead had the Russian acronym OGCh. It consisted of an SU equipment unit which oriented the spacecraft in orbit and autonomously determined when to make the braking manoeuvre to bring the re-entry vehicle down from orbit. The SU included an inertial navigation system and a radar altimeter which measured the altitude of the orbit and thereby determined when to make the braking manoeuvre. A solid fuel cartridge then spun up the turbine assembly of the liquid propellant (N2O4/UDMH) braking engine. Orientation was by 4 + 4 thrusters using turbine exhaust gases.

Manufacturer: Yangel. Launches: 25. Failures: 2. Success Rate: 92.00%. First Launch Date: 1965-03-05. Last Launch Date: 1971-08-08. Launch data is: incomplete. LEO Payload: 1,700 kg (3,700 lb). to: 150 km Orbit. Associated Spacecraft: OGCh. Liftoff Thrust: 2,366.000 kN (531,897 lbf). Total Mass: 182,000 kg (401,000 lb). Core Diameter: 3.00 m (9.80 ft). Total Length: 32.60 m (106.90 ft). Span: 3.35 m (10.99 ft). Standard warhead mass: 1,700 kg (3,700 lb). Maximum range: 40,000 km (24,000 mi). Number Standard Warheads: 1. Standard RV: 8F021. Standard warhead yield: 5,000 KT. Standard warhead CEP: 1.10 km (0.60 mi). Boost Propulsion: Storable liquid rocket, N2O4/UDMH. Boost engine: RD-251. Cruise Propulsion: Storable liquid rocket, N2O4/UDMH. Cruise engine: RD-252. Cruise Thrust: 940.400 kN (211,410 lbf). Guidance: Inertial.

• Stage Number: 1. 1 x Stage: R-36-0-1. Gross Mass: 125,000 kg (275,000 lb). Empty Mass: 8,500 kg (18,700 lb). Thrust (vac): 2,640.000 kN (593,490 lbf). Isp: 301 sec. Burn time: 120 sec. Isp(sl): 269 sec. Diameter: 3.00 m (9.80 ft). Span: 3.00 m (9.80 ft). Length: 18.90 m (62.00 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: RD-251. Status: Out of production.

• Stage Number: 2. 1 x Stage: R-36-0-2. Gross Mass: 48,000 kg (105,000 lb). Empty Mass: 5,000 kg (11,000 lb). Thrust (vac): 955.991 kN (214,915 lbf). Isp: 317 sec. Burn time: 160 sec. Diameter: 3.00 m (9.80 ft). Span: 3.00 m (9.80 ft). Length: 9.40 m (30.80 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: RD-252. Status: Out of production.

1962 April 16 - Launch Vehicle: N1, R-36, R-36-O, R-56.

• N1, R-36, R-36-O, and R-56 rockets authorised. Nation: USSR. Decree 'On Important Development of Intercontinental Ballistic and Global Missiles and Carriers-Rockets for Space Objects--work on the N1, R-36, R-36-O, and R-56' was issued. References: 474.

• R-36 'sealed round' version development authorised. Nation: USSR. State Committee for Defence Technology (GKOT) Decree 'On Detailed Work on Ampulized R-36 and R-36-O Missiles--design work on the R-36 and R-36-O missiles' was issued. References: 474.

• First attempted launch of Fractional Orbital Bombardment System booster. Nation: USSR. Mass: 1,700 kg (3,700 lb). Spacecraft: OGCh. Agency: RVSN. COSPAR: F19650305. A fire broke out during fuelling and the rocket exploded, seriously damaging the launch pad at Area 67. References: 279.

• Development of R-36-O and Tsyklon launch vehicles authorised Nation: USSR. Spacecraft: IS-A, US-A, OGCh. Decree 'On Creation of an R-36 Based Carrier Rocket for Launching the IS and US KA--start of work on an R-36-based launch vehicle for the IS and US programs' was issued. After Khrushchev was ousted from power, Chelomei's projects were examined by an expert commission under M V Keldysh. It was found that Yangel’s R-36 rocket was superior to Chelomei’s UR-200. The UR-200 was cancelled; the IS and US satellites would be launched by the R-36 11K67. The Tsyklon 2 definitive operational version replaced the 11K67 launch vehicle from 1969.References: 474.

• OGCh No. 01L Nation: USSR. Mass: 1,700 kg (3,700 lb). Spacecraft: OGCh. Agency: RVSN. Apogee: 200 km (120 mi). COSPAR: U651216A. First suborbital test of the FOBS system. Impacted within specification CEP in target zone. References: 279.

• OGCh No. 02L Nation: USSR. Mass: 1,700 kg (3,700 lb). Spacecraft: OGCh. Agency: RVSN. Apogee: 200 km (120 mi). COSPAR: U660205A. Second suborbital test of the FOBS system. References: 279.

• OGCh No. 03L Nation: USSR. Mass: 1,700 kg (3,700 lb). Spacecraft: OGCh. Agency: RVSN. Apogee: 0 km ( mi). COSPAR: U660316A. Last of three suborbital flight tests of the FOBS system. The second stage of the booster placed the third stage and dummy warhead on a depressed trajectory with a range of 8500 km but an altitude of only 220 km (versus 800 to 1200 km for an optimum ballistic trajectory). The third stage than executed a 180 degree turn and its engines were fired to further brake the warhead to an impact on the Kamchatka peninsula. The second stage meanwhile continued on to reentry over the Pacific Ocean.References: 279.

• OGCh No. 04L Nation: USSR. Mass: 1,700 kg (3,700 lb). Spacecraft: OGCh. Agency: RVSN. COSPAR: U660519A. Possible suborbital test of FOBS booster or failed FOBS test. Not mentioned as FOBS-related in contemporary CIA assessments. References: 279.

• OGCh Nation: USSR. Mass: 1,700 kg (3,700 lb). Class: Military. Type: FOBS. Spacecraft: OGCh. Agency: RVSN. Perigee: 138 km (85 mi). Apogee: 792 km (492 mi). Inclination: 49.60 deg. Period: 93.90 min. COSPAR: 1966-088A. USAF Sat Cat: 2437. Decay Date: 1966-11-11. First attempted orbital Fractional Orbital Bombardment System test. The second stage of the booster placed the third stage and dummy warhead into a 214 km x 523 km parking orbit. altitude. The third stage was evidently wrongly oriented, and instead of braking the warhead into an impact at Kapustin Yar, boosted it into a higher 280 km x 1,010 km orbit. The dummy warhead seperated but was commanded to self destruct, resulting in over 100 catalogued orbiting objects.References: 1, 2, 5, 6.

• OGCh Nation: USSR. Mass: 1,700 kg (3,700 lb). Class: Military. Type: FOBS. Spacecraft: OGCh. Agency: RVSN. Perigee: 504 km (313 mi). Apogee: 767 km (476 mi). Inclination: 49.10 deg. Period: 97.43 min. COSPAR: 1966-101AS. USAF Sat Cat: 2931. Decay Date: 1976-04-26. Second attempted orbital Fractional Orbital Bombardment System test. failure - self destruct charge was detonated, resulting in 50 catalogued orbiting objects. No impact of the dummy warhead in the Kapustin Yar impact zone. References: 279.

• Cosmos 139 Nation: USSR. Mass: 1,700 kg (3,700 lb). Class: Military. Type: FOBS. Spacecraft: OGCh. Agency: RVSN. Perigee: 144 km (89 mi). Apogee: 210 km (130 mi). Inclination: 49.70 deg. Period: 88.00 min. COSPAR: 1967-005A. USAF Sat Cat: 2656. Decay Date: 1967-01-25. Third orbital Fractional Orbital Bombardment System test. First apparently successful test. The warhead was braked to an impact in the Kapustin Yar range. References: 1, 2, 5, 6.

• OGCh Nation: USSR. Mass: 1,700 kg (3,700 lb). Spacecraft: OGCh. Agency: RVSN. COSPAR: F670322A. References: 279.

• Cosmos 160 Nation: USSR. Mass: 1,700 kg (3,700 lb). Class: Military. Type: FOBS. Spacecraft: OGCh. Agency: RVSN. Perigee: 137 km (85 mi). Apogee: 177 km (109 mi). Inclination: 49.70 deg. Period: 87.60 min. COSPAR: 1967-047A. USAF Sat Cat: 2806. Decay Date: 1967-05-18. Fractional Orbital Bombardment system test. References: 1, 2, 5, 6.

• Cosmos 169 Nation: USSR. Mass: 1,700 kg (3,700 lb). Class: Military. Type: FOBS. Spacecraft: OGCh. Agency: RVSN. Perigee: 135 km (83 mi). Apogee: 200 km (120 mi). Inclination: 49.70 deg. Period: 87.80 min. COSPAR: 1967-069A. USAF Sat Cat: 2878. Decay Date: 1967-07-17. Fractional Orbital Bombardment system test. References: 1, 2, 5, 6.

• US Project reassigned; R-36-O booster development approved; Yantar-2K and Zvevda 7K-VI approved. Nation: USSR. Spacecraft: US-A, US-P, Yantar-2K, Yantar-4K1, Soyuz VI. Decree 715-240 'On the Creation of Space Systems for Naval Reconnaissance Comprising the US sat and the R-36-based booster -further work on the US naval reconnaissance satellite, approval of work on the Yantar-2K, and course of work on 7K-VI Zvezda'.

  An entire family of Yantar spacecraft was proposed by Kozlov’s design bureau during the initial development; information on two film return models has been declassified. Yantar was initially derived from the Soyuz spacecraft, including systems developed for the Soyuz VI military model. During design and development this changed until it had very little in common with Soyuz.

  Following numerous problems in the first flight tests of the Soyuz 7K-OK, Kozlov ordered a complete redesign of the 7K-VI manned military spacecraft. The new spacecraft, with a crew of two, would have a total mass of 6.6 tonnes and could operate for a month in orbit. The new design switched the positions of the Soyuz descent module and the orbital modules and was 300 kg too heavy for the standard 11A511 launch vehicle. Therefore Kozlov designed a new variant of the Soyuz launch vehicle, the 11A511M. The project was approved by the Central Committee of the Communist Party, with first flight to be in 1968 and operations to begin in 1969. The booster design, with unknown changes to the basic Soyuz, did not go into full production.References: 474.

• Cosmos 170 Nation: USSR. Mass: 1,700 kg (3,700 lb). Class: Military. Type: FOBS. Spacecraft: OGCh. Agency: RVSN. Perigee: 141 km (87 mi). Apogee: 199 km (123 mi). Inclination: 49.60 deg. Period: 87.90 min. COSPAR: 1967-074A. USAF Sat Cat: 2902. Decay Date: 1967-07-31. Fractional Orbital Bombardment system test. References: 1, 2, 5, 6.

• Cosmos 171 Nation: USSR. Mass: 1,700 kg (3,700 lb). Class: Military. Type: FOBS. Spacecraft: OGCh. Agency: RVSN. Perigee: 138 km (85 mi). Apogee: 177 km (109 mi). Inclination: 49.60 deg. Period: 87.60 min. COSPAR: 1967-077A. USAF Sat Cat: 2911. Decay Date: 1967-08-08. Fractional Orbital Bombardment system test. References: 1, 2, 5, 6.

• Cosmos 178 Nation: USSR. Mass: 1,700 kg (3,700 lb). Class: Military. Type: FOBS. Spacecraft: OGCh. Agency: RVSN. Perigee: 138 km (85 mi). Apogee: 258 km (160 mi). Inclination: 49.70 deg. Period: 88.40 min. COSPAR: 1967-089A. USAF Sat Cat: 2951. Decay Date: 1967-09-19. Fractional Orbital Bombardment system test. References: 1, 2, 5, 6.

• Cosmos 179 Nation: USSR. Mass: 1,700 kg (3,700 lb). Class: Military. Type: FOBS. Spacecraft: OGCh. Agency: RVSN. Perigee: 139 km (86 mi). Apogee: 207 km (128 mi). Inclination: 49.60 deg. Period: 87.90 min. COSPAR: 1967-091A. USAF Sat Cat: 2962. Decay Date: 1967-09-22. Fractional Orbital Bombardment system test. References: 1, 2, 5, 6.

• Cosmos 183 Nation: USSR. Mass: 1,700 kg (3,700 lb). Class: Military. Type: FOBS. Spacecraft: OGCh. Agency: RVSN. Perigee: 140 km (80 mi). Apogee: 306 km (190 mi). Inclination: 49.60 deg. Period: 89.00 min. COSPAR: 1967-099A. USAF Sat Cat: 3001. Decay Date: 1967-10-18. Fractional Orbital Bombardment system test. References: 1, 2, 5, 6.

• Cosmos 187 Nation: USSR. Mass: 1,700 kg (3,700 lb). Class: Military. Type: FOBS. Spacecraft: OGCh. Agency: RVSN. Perigee: 143 km (88 mi). Apogee: 301 km (187 mi). Inclination: 49.60 deg. Period: 88.90 min. COSPAR: 1967-106A. USAF Sat Cat: 3016. Decay Date: 1967-10-28. Fractional Orbital Bombardment System test. References: 1, 2, 5, 6.

• Cosmos 218 Nation: USSR. Mass: 1,700 kg (3,700 lb). Class: Military. Type: FOBS. Spacecraft: OGCh. Agency: RVSN. Perigee: 123 km (76 mi). Apogee: 162 km (100 mi). Inclination: 49.60 deg. Period: 87.30 min. COSPAR: 1968-037A. USAF Sat Cat: 3217. Decay Date: 1968-04-25. Fractional Orbital Bombardment System test. References: 1, 2, 5, 6.

• OGCh Nation: USSR. Mass: 1,700 kg (3,700 lb). Class: FOBS. Spacecraft: OGCh. Agency: RVSN. COSPAR: 1968-U01xx. Probable suborbital test of Fractional Orbital Bombardment System. References: 279.

• OGCh Nation: USSR. Mass: 1,700 kg (3,700 lb). Class: FOBS. Spacecraft: OGCh. Agency: RVSN. COSPAR: 1968-U02xx. Probable suborbital test of Fractional Orbital Bombardment System. References: 279.

• Cosmos 244 Nation: USSR. Mass: 1,700 kg (3,700 lb). Class: Military. Type: FOBS. Spacecraft: OGCh. Agency: RVSN. Perigee: 140 km (80 mi). Apogee: 158 km (98 mi). Inclination: 49.60 deg. Period: 87.40 min. COSPAR: 1968-082A. USAF Sat Cat: 3449. Decay Date: 1968-10-02. Fractional Orbital Bombardment System test. References: 1, 2, 5, 6.

• R-36-O rocket accepted into military service. Nation: USSR. Decree 'On adoption of the R-36-O into armaments' was issued. References: 474.

• Cosmos 298 Nation: USSR. Mass: 1,700 kg (3,700 lb). Class: Military. Type: FOBS. Spacecraft: OGCh. Agency: RVSN. Perigee: 127 km (78 mi). Apogee: 162 km (100 mi). Inclination: 49.60 deg. Period: 87.30 min. COSPAR: 1969-077A. USAF Sat Cat: 4092. Decay Date: 1969-09-15. Fractional Orbital Bombardment System test. References: 1, 2, 5, 6.

• Cosmos 354 Nation: USSR. Mass: 1,700 kg (3,700 lb). Class: Military. Type: FOBS. Spacecraft: OGCh. Agency: RVSN. Perigee: 137 km (85 mi). Apogee: 165 km (102 mi). Inclination: 49.60 deg. Period: 87.50 min. COSPAR: 1970-056A. USAF Sat Cat: 4481. Decay Date: 1970-07-28. Fractional Orbital Bombardment System test. References: 1, 2, 5, 6.

• Cosmos 365 Nation: USSR. Mass: 1,700 kg (3,700 lb). Class: Military. Type: FOBS. Spacecraft: OGCh. Agency: RVSN. Perigee: 145 km (90 mi). Apogee: 173 km (107 mi). Inclination: 49.50 deg. Period: 87.70 min. COSPAR: 1970-076A. USAF Sat Cat: 4556. Decay Date: 1970-09-25. Fractional Orbital Bombardment System test. References: 1, 2, 5, 6.

• Cosmos 433 Nation: USSR. Mass: 1,700 kg (3,700 lb). Class: Military. Type: FOBS. Spacecraft: OGCh. Agency: RVSN. Perigee: 112 km (69 mi). Apogee: 299 km (185 mi). Inclination: 49.40 deg. Period: 88.50 min. COSPAR: 1971-068A. USAF Sat Cat: 5402. Decay Date: 1971-08-09. Fractional Orbital Bombardment System test. References: 1, 2, 5, 6.

• McDowell, Jonathan, Jonathan's Space Home Page, Harvard University, 1997-present. Jonathan McDowell's complete on-line listing of all objects orbited and over 20,000 rocket launches Accessed at: http://www.planet4589.org/jsr.html.

• Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991 (succeeded by 2000 edition). ISBN: 1563473534. Superseded by the later editions. More at amazon.com...

• Zak, Anatoly, Spaceflight, "Cosmos Launcher", 1996, Volume 38, page 416.

• Agapov, V, Novosti Kosmonavtiki, "K zapusku pervovo ISZ serii 'DS'", 1997, Issue 6.

• Placard, TsNIIMASH Museum, .

• Pervov, Mikhail, Raketnoye Oruzhiye RVSN, Violanta, Moscow, 1999.. Narrative overview of the missiles of the Russian strategic missile forces.

• Karpenko, A V, Utkin, A F and Popov,A D, Otechestvenniye strategischeskiye raketnoye kompleks, Sankt-Peterburg: Nevskii bastion; Gangut 1999.. Well-illustrated encyclopedia of the missiles of the Russian strategic missile forces.