UR-100

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Intercontinental ballistic missile. IOC: 1966. Country: Russia. Status: Retired 1984. Other Designations: RS-10. Department of Defence Designation: SS-11 Mod.1. ASCC Reporting Name: Sego. Article Number: 8K84. Manufacturer's Designation: UR-100. Launch System: 15P784. Complex: 8K84. Missile: 15A10.

The UR-100 lightweight ICBM was the Soviet answer to the US Minuteman and was deployed in larger numbers than any other in history. It remained an enigma outside of intelligence circles in the West until after the collapse of the Soviet Union. It allowed the Soviet Union to match, and then surpass the United States in strategic deterrent capability. As such it was Vladimir Chelomei's crowning legacy to his country.

Official go-ahead for development of the 8K84 was on 30 March 1963 (Russian sources say the 8K84 missile put into production was not related to Chelomei's original actual UR-100 design. However this correlation came into general acceptance retroactively). The decree called for a silo-launched missile that could be stored in a fuelled condition for at least five years as a 'certified round', ready to be launched at short notice. Submarine-launched and anti-ballistic missile versions of the missile were also to be designed, but no pad-launched variant was envisioned. Chelomei had already been working on the missile for several years, with tests of the planned radio-guidance system starting in 1962. The 15P784 silo was designed by Spetsmash.

Such was the urgency to overcome the massive US superiority in ICBM's, surveys were already underway to identify suitable sites for missile silos accessible by rail spurs. The teams consisted of geologic and geodesic specialists under the leadership of Yevgeniy Yevtigneyev. Their missions were so secret they used the cover and resources of Uralgaz and the leader could only identify himself as a 'general from Moscow'. The teams travelled by train, truck and horse to reach the potential silo locations. Construction of launch silos at the selected locations all over the Soviet Union began in 1964 even before the missile was tested. This was a huge industrial enterprise, the construction of the 1130 silos for the UR-100 and 308 for the R-36 occupying a peak workforce of 650,000 until 1973. Construction of these silos involved a total cost of one billion roubles and the removal of 120 million cubic metres of earth.

There was an enormous amount of completely new technology to be mastered. This included not just the sealed missile (which had to resist corrosive propellants 20,000 times more aggressive than those used previously for many years), but the integrated transport/storage container and silo ejection technique. Production of the missile itself was conducted at three factories -- the Khrunichev facility in Moscow; Factory 166 (later PO Polyot) in Omsk; and Factory 47 (later PO Strela) in Orenburg.

One prototype command point and ten missile silos were built at Baikonur for the flight tests. 60 trials flights were conducted from 19 April 1965 to 27 October 1966, with the first silo launch on 17 July 1965. The first regiments at Bershet and Drovyanaya became operational on 17 July 1966, before the test series was completed. 90 silos were operational by the end of 1966 and the missile and silo were accepted for military service on 21 July 1967.

In field deployment a single hardened command point controlled ten silos. The silos could resist an over-pressure of 20 atmospheres, equivalent to explosion of a one megaton bomb 1300 metres from the silo. Deployment rose to 540 by 1968, 840 by 1970, and 940 in 1961. By 1974 the peak of 1030 UR-100 silos were in operation. By that time 106 UR-100's had been launched in trials flights and another 54 flown from military bases. The last UR-100 was withdrawn from service in 1988. However UR-100's were replaced in their silos by UR-100M's, UR-100K's, UR-100N's, UR-100NU's, and even MR-UR-100's by another manufacturer, proving the worth of the containerised missile concept.

The UR-100 was the first Soviet ICBM with a three minute reaction time - from key turn to lift-off - a huge accomplishment for a liquid propellant vehicle. To make this reaction time possible the vehicle stayed fuelled throughout its guaranteed storage lifetime of five years (extended to first 8, then 10, then 17 years based on in-service tests). This was achieved by encapsulation of the missile in a container in which this missile stayed from production until launch. The container was designed by OKB-52 Filial 2, weighed 14.4 tonnes, had a diameter of 2.7 meters, and a length of 19.5 meters. The missile was mounted on rails within the container and internal plumbing necessary for start-up of the missile was sealed within the container.

The 8S816 first stage and 8S817 second stage were powered by Kosberg and Izotov engines, respectively. Since terminal velocity at the end of second stage burn was only 7.12 km/sec the UR-100 was never adapted for space launches. The missile was produced in three optional configurations (not modifications - only the payload was changed to convert from one configuration to another):

ICBM with range up to 11,000 km with a light (770 kg) warhead, re-entry vehicle designed by Kocaryats at VNIITF and warhead by Arazamas-16.
MRBM (up to 4000 km) with a heavy (1750 kg) warhead, designed at VNIITF with warhead by Chelyabinsk-70.
ABM vehicle 'Taran' with range not less than 2000 km

The guidance system by Kuznetsov and inertial navigation system by Pilyugin were designed to work with any of these configurations and the vehicle could be converted from one to another within 24 hours. Missiles could be programmed for launch plus or minus 30 degrees from their standard corridor. The Palma countermeasures suite by Gerasimenko at NII-108 was fitted to spoof enemy anti-ballistic missile defences.

Propellant tanks were constructed of AMG-6 aluminium alloy. The rocket was normally painted white, and the light warhead version had a strict conic shape. The heavy warhead was longer, but with the same base diameter. The first five launches of the missile from Baikonur used radio-inertial guidance with a radio-command correction system by Ryazinskiy. Later testing gave the military confidence that the pure inertial guidance was precise enough, and the radio receiver was removed in production models.

Work on the Taran ABM version began in 1962-1963. The concept was ingenious, in that offensive missiles could be turned into defensive missiles in response to changes in enemy posture. For use as an ABM the launch complex need some additional equipment and the missile carried a 10 megaton warhead. Incoming missile tracking for Taran would be provided by the TsSO-S radar system located 500 km from Moscow. Taran would be used with the shorter-range A-350 missile developed for the defence of Moscow as part of a layered defence. However Taran could defend, from a single basing area, the most heavily populated area of the Soviet Union, from Leningrad to Moscow. However after the fall of Khrushchev, Chelomei's patron, further work on the Taran system was abandoned.

In total, 12 Strategic Rocket Forces divisions were equipped with the various models of the basic UR-100 (UR-100, UR-100M, UR-100K, UR-100U). Production of these versions extended from 1964 to 1974. There were a total of 162 test and operational test launches of these models. Of these, 67 were tests of the UR-100U. UR-100 artefacts may be found at Orevo, which has a complete sectioned missile, and Baikonur, which has models and photographs.

Manufacturer: Chelomei. Launches: 282. Failures: 21. Success Rate: 92.55%. First Launch Date: 1965-01-01. Last Launch Date: 1984-01-01. Launch data is: incomplete. Apogee: 1,000 km (600 mi). Liftoff Thrust: 785.000 kN (176,475 lbf). Total Mass: 41,410 kg (91,290 lb). Core Diameter: 2.00 m (6.50 ft). Total Length: 16.93 m (55.53 ft). Span: 2.00 m (6.50 ft). Standard warhead mass: 770 kg (1,690 lb). Maximum range: 11,000 km (6,000 mi). Number Standard Warheads: 1. Standard RV: 15F842. Standard warhead yield: 500 KT. Standard warhead CEP: 1.40 km (0.80 mi). Alternate warhead mass: 1,750 kg (3,850 lb). Maximum range with alternate warhead: 4,000 km (2,400 mi). Number Alternate Warheads: 1. Alternate warhead yield: 1,100 KT. Alternate warhead CEP: 1.00 km (0.60 mi). Boost Propulsion: Storable liquid rocket, N2O4/UDMH. Boost engine: RD-0216. Cruise Propulsion: Storable liquid rocket, N2O4/UDMH. Cruise engine: 8D423. Guidance: Inertial+Radio correction. Total Number Built: 790.

Stage1: 1 x 8S816. Gross Mass: 32,799 kg (72,309 lb). Empty Mass: 3,000 kg (6,600 lb). Motor: 4 x RD-0216. Thrust (vac): 868.800 kN (195,314 lbf). Isp: 310 sec. Burn time: 102 sec. Length: 10.00 m (32.00 ft). Diameter: 1.60 m (5.20 ft). Propellants: N2O4/UDMH.

Stage2: 1 x 8S817. Gross Mass: 8,611 kg (18,984 lb). Empty Mass: 900 kg (1,980 lb). Motor: 1 x 8D423. Thrust (vac): 131.448 kN (29,551 lbf). Isp: 325 sec. Burn time: 184 sec. Length: 6.69 m (21.95 ft). Diameter: 2.00 m (6.50 ft). Propellants: N2O4/UDMH.

Version:

UR-100M.
8K84 back
Credit - © Mark Wade
IOC: 1970. Other Designations: RS-10. Department of Defence Designation: SS-11 Mod.2. ASCC Reporting Name: Sego. Article Number: 8K84M. Alternate Designation: UR-100M. Launch System: 15P084. Complex: 8K84UTTKh.

The 8K84M was an improved version of the UR-100 with an improved empty mass fraction, a new guidance system, countermeasures capability, and post-boost manoeuvrability to defeat enemy anti-ballistic missile systems. Development was authorised on 9 December 1965. Twelve trial flights were conducted between 23 July 1969 and 15 March 1971. The system was formally accepted by the military on 3 October 1972. The first regiment became operational at Khmelnitskiy on 1 March 1970.

Tests were made with a radar system to provide improved accuracy with a one megaton warhead at 9200 km range, but this was not adopted for service. Although this missile is often referred to as the UR-100M, this designation was applied within the design bureau to a naval version of the UR-100 developed by Chelomei in 1962-1964, but not selected for full development or production.

Launches: 18. First Launch Date: 1970-01-01. Last Launch Date: 1984-01-01. Apogee: 1,000 km (600 mi). Liftoff Thrust: 876.000 kN (196,932 lbf). Total Mass: 50,100 kg (110,400 lb). Core Diameter: 2.00 m (6.50 ft). Total Length: 18.90 m (62.00 ft). Span: 2.00 m (6.50 ft). Standard warhead mass: 1,050 kg (2,310 lb). Maximum range: 13,000 km (8,000 mi). Number Standard Warheads: 1. Standard warhead yield: 1,200 KT. Standard warhead CEP: 1.10 km (0.60 mi). Boost Propulsion: Storable liquid rocket, N2O4/UDMH. Boost engine: RD-0216. Cruise Propulsion: Storable liquid rocket, N2O4/UDMH. Cruise engine: 8D423. Guidance: Inertial. Total Number Built: 590.

Stage1: 1 x 8S816. Gross Mass: 32,799 kg (72,309 lb). Empty Mass: 3,000 kg (6,600 lb). Motor: 4 x RD-0216. Thrust (vac): 868.800 kN (195,314 lbf). Isp: 310 sec. Burn time: 102 sec. Length: 10.00 m (32.00 ft). Diameter: 1.60 m (5.20 ft). Propellants: N2O4/UDMH.

Stage2: 1 x 8S817. Gross Mass: 8,611 kg (18,984 lb). Empty Mass: 900 kg (1,980 lb). Motor: 1 x 8D423. Thrust (vac): 131.448 kN (29,551 lbf). Isp: 325 sec. Burn time: 184 sec. Length: 6.69 m (21.95 ft). Diameter: 2.00 m (6.50 ft). Propellants: N2O4/UDMH.

Version:

UR-100K.
UR-100
Credit - © Mark Wade
IOC: 1973. Other Designations: RS-10M. Department of Defence Designation: SS-11 Mod.3. ASCC Reporting Name: Sego. Article Number: 15A20. Manufacturer's Designation: UR-100K. Alternate Designation: 8K84K. Launch System: 15P884. Complex: 15A20.

Development of the UR-100K began at the end of the 1960's, with the objective of fielding a version of the 8K84M with further improvements in accuracy but also capable of delivering three separate (but not independently targeted) re-entry vehicles. A two-piece nose fairing separated at the end of the second-stage engine burn to expose the warheads. Pyrotechnic charges then separated the re-entry vehicles, which fell in a triangular patter about 1.5 to 2.0 km around the aim-point. Decoys were mounted on the second stage below the warheads and were deployed after they had separated. American National Security Adviser Kissinger complained in the SALT-1 arms talks that the silos and command points of this version of this missile could not be distinguished by American reconnaissance assets from the single-warhead version. However in practice there were internal differences between the missiles and they could not be interchanged as the Americans claimed. Trials began on 2 February 1971 and were completed on 24 November 1971.

Launches: 77. Failures: 3. Success Rate: 96.10%. First Launch Date: 1969-01-01. Last Launch Date: 1977-01-01. Apogee: 1,000 km (600 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 50,100 kg (110,400 lb). Core Diameter: 2.00 m (6.50 ft). Total Length: 18.95 m (62.17 ft). Span: 2.00 m (6.50 ft). Standard warhead mass: 1,208 kg (2,663 lb). Maximum range: 10,600 km (6,500 mi). Number Standard Warheads: 3. Standard RV: MRV. Standard warhead yield: 350 KT. Standard warhead CEP: 1.09 km (0.67 mi). Alternate warhead mass: 1,200 kg (2,600 lb). Maximum range with alternate warhead: 12,000 km (7,000 mi). Number Alternate Warheads: 1. Alternate warhead yield: 1,300 KT. Alternate warhead CEP: 1.09 km (0.67 mi). Boost Propulsion: Storable liquid rocket, N2O4/UDMH. Cruise Propulsion: Storable liquid rocket, N2O4/UDMH. Guidance: Inertial. Total Number Built: 220.

Stage1: 1 x 8S816. Gross Mass: 32,799 kg (72,309 lb). Empty Mass: 3,000 kg (6,600 lb). Motor: 4 x RD-0216. Thrust (vac): 868.800 kN (195,314 lbf). Isp: 310 sec. Burn time: 102 sec. Length: 10.00 m (32.00 ft). Diameter: 1.60 m (5.20 ft). Propellants: N2O4/UDMH.

Stage2: 1 x 8S817. Gross Mass: 8,611 kg (18,984 lb). Empty Mass: 900 kg (1,980 lb). Motor: 1 x 8D423. Thrust (vac): 131.448 kN (29,551 lbf). Isp: 325 sec. Burn time: 184 sec. Length: 6.69 m (21.95 ft). Diameter: 2.00 m (6.50 ft). Propellants: N2O4/UDMH.

Version:

UR-100M SLBM.
Missile silo model
Credit - © Mark Wade
Status: Design 1964. Manufacturer's Designation: UR-100M. Launch System: D-8.

The UR-100M designation was used for a naval version of the UR-100, developed by Chelomei in 1962-1964. This would fit in the Navy's D-8 launch system. It was rejected in favour of the R-29 from Makeyev, who became the Navy's traditional supplier of SLBM's. Makeyev submitted Chelomei's proposal to withering criticism at a Ministry of Defence meeting in July 1964. The UR-100M was to have radio correction to achieve the necessary accuracy, while Makeyev's missile used autonomous celestial navigation to correct the inertial guidance system. Chelomei envisioned basing mainly on barges or submerged buoys in order to have a known accurate launch position, while Makeyev proposed basing on mobile submarines. Khrushchev at the time was pushing for basing of missile on icebergs as a less-costly alternative to nuclear submarines. The Soviet Navy rejected these alternatives in favour of the same kind of submarine-based deterrent forces the Americans were deploying.

The 8K84M version of the basic UR-100 missile, developed in 1965-1972, is sometimes referred to by Soviet histories as the 'UR-100M' as well.

Apogee: 1,000 km (600 mi). Liftoff Thrust: 785.000 kN (176,475 lbf). Total Mass: 41,410 kg (91,290 lb). Core Diameter: 2.00 m (6.50 ft). Total Length: 16.93 m (55.53 ft). Span: 2.00 m (6.50 ft). Standard warhead mass: 770 kg (1,690 lb). Maximum range: 11,000 km (6,000 mi). Number Standard Warheads: 1. Standard RV: 15F842. Standard warhead yield: 500 KT. Standard warhead CEP: 1.40 km (0.80 mi). Alternate warhead mass: 1,750 kg (3,850 lb). Maximum range with alternate warhead: 4,000 km (2,400 mi). Number Alternate Warheads: 1. Alternate warhead yield: 1,100 KT. Alternate warhead CEP: 1.00 km (0.60 mi). Boost Propulsion: Storable liquid rocket, N2O4/UDMH. Boost engine: RD-0216. Cruise Propulsion: Storable liquid rocket, N2O4/UDMH. Cruise engine: 8D423. Guidance: Inertial+Radio correction.

Stage1: 1 x 8S816. Gross Mass: 32,799 kg (72,309 lb). Empty Mass: 3,000 kg (6,600 lb). Motor: 4 x RD-0216. Thrust (vac): 868.800 kN (195,314 lbf). Isp: 310 sec. Burn time: 102 sec. Length: 10.00 m (32.00 ft). Diameter: 1.60 m (5.20 ft). Propellants: N2O4/UDMH.

Stage2: 1 x 8S817. Gross Mass: 8,611 kg (18,984 lb). Empty Mass: 900 kg (1,980 lb). Motor: 1 x 8D423. Thrust (vac): 131.448 kN (29,551 lbf). Isp: 325 sec. Burn time: 184 sec. Length: 6.69 m (21.95 ft). Diameter: 2.00 m (6.50 ft). Propellants: N2O4/UDMH.

Version:

UR-100U. IOC: 1972. Other Designations: RS-10MUTTKh. Department of Defence Designation: SS-11 Mod.4. ASCC Reporting Name: Sego. Article Number: 15A20U. Manufacturer's Designation: UR-100U. Launch System: 15P020. Complex: 15A20U.

The UR-100U was a development of the UR-100K with improved shock isolation in the silo. A competition for an improved silo design was held in 1969 and won by Vladimir Baryshev's team at OKB-52 Filial 2. Tests began in this period of improved silo designs at the Semipalatinsk nuclear proving ground. These improvements included plastic shock absorbers to isolate the missile from blast, shielded command antennae, and 'cold absorbers' that could absorb the heat of nearby nuclear explosions. The resulting silo/container was the subject of 15 new patents and was considered by the Americans as the most blast-resistant in the world. Flight trials were conducted from 1 June 1971 to January 1973. The missile was accepted by the military on 26 September 1974 and finally retired in 1993. In service a regiment consisted of a control point and ten silos. By 1987 440 UR-100K and UR-100U's had been deployed to missiles fields at Kozelsk, Teikovo, Bershet, Gladkaya, Drovyanaya, Svobodniy, and Yasnaya. Of these a total of 120 were in silos re built to the new design. These were later filled with UR-100N and UR-100NU missiles before being retired in the 1990's.

Launches: 20. First Launch Date: 1971-01-01. Last Launch Date: 1976-01-01. Apogee: 1,000 km (600 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 50,100 kg (110,400 lb). Core Diameter: 2.00 m (6.50 ft). Total Length: 18.95 m (62.17 ft). Span: 2.00 m (6.50 ft). Standard warhead mass: 1,208 kg (2,663 lb). Maximum range: 10,600 km (6,500 mi). Number Standard Warheads: 3. Standard RV: MRV. Standard warhead yield: 350 KT. Standard warhead CEP: 1.09 km (0.67 mi). Alternate warhead mass: 1,200 kg (2,600 lb). Maximum range with alternate warhead: 12,000 km (7,000 mi). Number Alternate Warheads: 1. Alternate warhead yield: 1,300 KT. Alternate warhead CEP: 1.09 km (0.67 mi). Boost Propulsion: Storable liquid rocket, N2O4/UDMH. Cruise Propulsion: Storable liquid rocket, N2O4/UDMH. Guidance: Inertial. Total Number Built: 220.

Stage1: 1 x 8S816. Gross Mass: 32,799 kg (72,309 lb). Empty Mass: 3,000 kg (6,600 lb). Motor: 4 x RD-0216. Thrust (vac): 868.800 kN (195,314 lbf). Isp: 310 sec. Burn time: 102 sec. Length: 10.00 m (32.00 ft). Diameter: 1.60 m (5.20 ft). Propellants: N2O4/UDMH.

Stage2: 1 x 8S817. Gross Mass: 8,611 kg (18,984 lb). Empty Mass: 900 kg (1,980 lb). Motor: 1 x 8D423. Thrust (vac): 131.448 kN (29,551 lbf). Isp: 325 sec. Burn time: 184 sec. Length: 6.69 m (21.95 ft). Diameter: 2.00 m (6.50 ft). Propellants: N2O4/UDMH.

UR-100 Chronology

February 1963 - Council of Fili The Soviet leadership reviewed missile development since the Pitsunda meeting. Both the Yangel R-26 and Chelomei UR-100 were proposed as small ICBM�s to be put into mass production as a counter to the American Minuteman. The UR-100 was an ampulised missile with a guaranteed ten-year storage life. Yangel had not solved the problems of long-term storage of corrosive storable fuel yet. Therefore Khrushchev, supported by Kozlov and Brezhnev, selected the UR-100. A decree for mass production was issued on 30 May 1963.

1964 September 24 - Khrushchev visits Baikonur Spacecraft: Voskhod, Berkut, LK-700. Flight: Voskhod 2. This was his last visit, just weeks before his overthrow. The Soviet leadership were shown the UR-100 and observed launches of the competing UR-200 and R-36. Khrushchev agreed with the decision to put the R-36 into production instead of Chelomei�s UR-200. He felt he couldn�t turn down Yangel a third time after approving Korolev�s N1 instead of Yangel�s R-56 and Chelomei�s UR-100 instead of Yangel�s R-26. Khrushchev decided to cancel Korolev�s badly behind schedule R-9A, even though Smirnov and Ustinov insisted they wanted it in their arsenal (in May 1965, after Khrushchev�s overthrow, this decision was reversed and the R-9A went into production).

Khrushchev also visited a secret space fair, with Korolev, Chelomei, Yangel, and Glushko presenting their rockets and spacecraft. Chelomei presented his UR-700 heavy lift design as an alternative to Korolev�s N1. This presentation was a surprise to Ustinov and Dementiev. Khrushchev ordered Chelomei to prepare a draft proposal for the design. Chelomei hoped that 12 to 18 months later, when the UR-700 draft project would be completed, the fallacy of Korolev�s N1 design would be apparent to all. Korolev�s N1 plans were also reviewed and approved at the meeting.

Over the two days, Khruschev witnessed five launches of rockets by Korolev, Yangel, and Chelomei, all of them successful. Gagarin and Belyayev explained the Vykhod spacecraft to him, and Leonov donned a spacesuit and demonstrated how he would exit into open space form the inflatable airlock and return thereafter. All went very well.

This was the last time Khrushchev saw the chief designers of the Soviet rocket industry. Despite his support for them not one of them visited him in his retirement.

1965 - Baikonur -. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1965 April 19 - 02:20 GMT - Baikonur LC130. UR-100 U106416-01 State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1965 May 20 - 03:45 GMT - Baikonur -. FAILURE: Failure. State trials missile test Agency: RVSN. Apogee: 0 km ( mi).

1965 June 19 - Baikonur -. FAILURE: Failure. State trials missile test Agency: RVSN. Apogee: 0 km ( mi).

1965 July 10 - Baikonur -. FAILURE: Failure. State trials missile test Agency: RVSN. Apogee: 0 km ( mi).

1965 July 17 - Baikonur LC131. UR-100 229420-01 FAILURE: Failure. State trials missile test Agency: RVSN. Apogee: 0 km ( mi).

1965 July 31 - Baikonur LC131. FAILURE: Failure. State trials missile test Agency: RVSN. Apogee: 0 km ( mi).

1965 September 17 - Baikonur LC131. FAILURE: Failure. State trials missile test Agency: RVSN. Apogee: 0 km ( mi).

1965 September 25 - Baikonur -. FAILURE: Failure. State trials missile test Agency: RVSN. Apogee: 0 km ( mi).

1965 November 3 - Baikonur -. FAILURE: Failure. State trials missile test Agency: RVSN. Apogee: 0 km ( mi).

1965 November 5 - Baikonur -. FAILURE: Failure. State trials missile test Agency: RVSN. Apogee: 0 km ( mi).

1965 November 30 - Baikonur -. FAILURE: Failure. State trials missile test Agency: RVSN. Apogee: 0 km ( mi).

1965 December 19 - Baikonur -. FAILURE: Failure. State trials missile test Agency: RVSN. Apogee: 0 km ( mi).

1965 December 30 - Baikonur -. FAILURE: Failure. State trials missile test Agency: RVSN. Apogee: 0 km ( mi).

1966 - Baikonur -. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1966 - Baikonur -. SLI missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1966 - Baikonur -. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1966 - Baikonur -. SLI missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1966 April 21 - Baikonur -. FAILURE: Failure. Joint flight trials launch Agency: RVSN. Apogee: 0 km ( mi).

1966 June 11 - Baikonur -. FAILURE: Failure. Joint flight trials launch Agency: RVSN. Apogee: 0 km ( mi).

1966 August 15 - Baikonur -. FAILURE: Failure. Joint flight trials launch Agency: RVSN. Apogee: 0 km ( mi).

1966 October 27 - Baikonur -. SLI Last operational test launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1967 - Baikonur -. Operational missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1967 - Baikonur -. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1967 - Baikonur -. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1967 January 25 - Baikonur -. FAILURE: Failure. Operational missile test Agency: RVSN. Apogee: 0 km ( mi).

1968 - Baikonur -. Operational missile test Agency: RVSN. Apogee: 1,000 km (600 mi).