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MR-UR-100
Credit - © Mark Wade
Intercontinental ballistic missile. IOC: 1975. Country: Ukraine. Status: Retired 1988. Other Designations: RS-16. Department of Defence Designation: SS-17 Mod 1 and Mod 2. ASCC Reporting Name: Spanker. Article Number: 15A15. Manufacturer's Designation: MR-UR-100. Launch System: 15P015. Missile: 15A15.

The Yangel MR-UR-100 was designed as a replacement for Chelomei's UR-100 at the end of its 10 year storage life. Although it could be installed in the same silos, it was 50% heavier. The competing design of Chelomei, the UR-100N, was also put into production when the Soviet hierarchy deadlocked and could not pick one design over the other.

The MR-UR-100 was Yangel's second attempt to get into production a competitor to Chelomei's UR-100 light ICBM. Design work began in 1964 after the R-36 had begun flight testing, thereby eliminating the leadership's grounds for prohibiting Yangel from working on the R-38. The concept was an ICBM to replace the UR-100 after it had exceeded its guaranteed storage life. Yangel envisioned a missile that would fit into the 15P084 missile silos built for the UR-100, but be heavier through use of a missile of maximum possible diameter. In order to allow this and permit the possibility of rapid reload, a gas generator was used to 'cold launch' the missile clear of the silo before the first stage engine ignited. The resulting payload increase would allow the missile to carry multiple independently-targeted warheads (MIRV's). Chelomei also proposed the larger UR-100N as a replacement, but launched using the traditional and less-expensive hot-launch technique.

The competition between the two chief designers led to a drama universally remarked upon in memoirs of Soviet rocketeers. Both design bureaux had powerful supporters in the Soviet leadership, and no consensus could be reached on which missile to put into production. The Yuzhnoye design was supported by Central Committee Secretary Ustinov, head of the VPK Military-Industrial Commission Smirnov, Mozhorin (Director of TNIIM), Tyulin (Deputy Commander MOM), and designers Glushko, and Pilyugin. Chelomei was supported by Marshal Grechko, Head of MOM Afanasyev, and designers Sergeyev, Barmin, Baryshev and V Kuznetsov.

Keldysh headed an expert commission to select a design, but the split within the technical community resulted in a deadlock. Premier Brezhnev finally made the Solomonic but extremely expensive decision at a leadership meeting at Stalin's old dacha at Yalta -- both would be built and deployed.

On 2 September 1969 a decree instructed KB Yuzhnoye to proceed with full development of the missile. The technical project was completed in 1969, with Utkin as the chief designer at Yuzhnoye.

The draft project for Glushko's RD-268 booster engine was completed in 1970. This was to be an upgrade of the RD-263 building-block of the R-36M's first stage. First engine tests were begun in March 1971.

In September 1970 MOM decreed that the missile must use a new 15P715P hardened silo design. This SM-SP-30 modification to the 15P084 silos was designed by TsKB-34 KBEM. It provided improved hardening against nearby nuclear detonations. The advanced project and a full-size mock-up for the modification had been completed in 1968. The design used shock absorbers and a container made of a special resin to allow the missile to survive in nearly every case unless the silo was in the crater of the enemy warhead explosion. The extra survivability came at a price -- conversion of a silo to use the MR-UR-100 cost three times more than converting it to use the UR-100N. Accordingly the MR-UR-100 would be deployed in only 1/7 the number of silos as its competitor.

Ground tests of the missile began in May 1971 at the Pavlograd Mechanical Factory, and began at Baikonur on 15 September 1972. For flight tests KBTM designed the 8P867 common pad facility that could be used with either the MR-UR-100 or R-36M. This was built as LC-67 at Tyuratam in 1970-1971, with the missile preparation facility being built at Area 42. A series of 30 trials launches were conducted from these pads and prototype silos from 26 December 1972 to 17 December 1974.

An official resolution was issued in October 1974 for the Yuzhnoye missile to go into production, although the work had already started a year earlier in anticipation of the decision. The missile was deployed in ten silos and one command point per regiment and the first regiment was already operational on 6 May 1975 at Vypolzovo. The missile was officially accepted for military service on 30 December 1975.

Deployment increased to 50 silos by the end of 1977, 100 by the end of 1978, and the final total of 150 in 1979. The missile was deployed in two fields at Bologoye and Kostroma. Only those missiles deployed after 11 November 1976 at Bologoye were emplaced in the superhardened silos. A training facility for missile crews was established at Belabanovo.

In 1979, during operational tests of missiles in-service, a problem was found with a high-frequency oscillation in the first stage motors. This severely degraded the missile's actual accuracy. Trials were made of modifications to fix the situation at the Perm Motor Machinery Factory between April and November 1977 under the direction of Ya M Sverdlov. The modification that solved the problem was officially accepted on 19 August 1980. It is not clear if the modification was made to field missiles, but the original model seems to have been replaced prematurely by its successor, the MR-UR-100UTTKh. Removal of MR-UR-100's from silos began in 1982 and all 150 were gone by the end of 1984.

The post-boost re-entry vehicle bus was separated from the missile's second stage by a solid propellant motor. It could be used to deliver a single warhead or dispense four warheads against separate targets. It also deployed countermeasures (decoys, jammers) to confuse enemy defences. The 71.1 tonne missile was fuelled with 63.2 tonnes of N2O4/UDMH storable propellants and had a guaranteed life of ten years, fuelled and ready to launch in its container within the silo.

Manufacturer: Yuzhnoye. Launches: 98. Failures: 8. Success Rate: 91.84%. First Launch Date: 1971-12-10. Last Launch Date: 1988-01-01. Launch data is: incomplete. Apogee: 1,000 km (600 mi). Liftoff Thrust: 1,147.000 kN (257,855 lbf). Total Mass: 71,100 kg (156,700 lb). Core Diameter: 2.25 m (7.38 ft). Total Length: 23.90 m (78.40 ft). Span: 2.25 m (7.38 ft). Standard warhead mass: 2,550 kg (5,620 lb). Maximum range: 10,320 km (6,410 mi). Number Standard Warheads: 1. Standard warhead yield: 3,600 KT. Standard warhead CEP: 0.45 km (0.27 mi). Alternate warhead mass: 2,600 kg (5,700 lb). Maximum range with alternate warhead: 10,200 km (6,300 mi). Number Alternate Warheads: 4. Alternate warhead yield: 300 KT. Alternate warhead CEP: 0.45 km (0.27 mi). Boost Propulsion: Storable liquid rocket, N2O4/UDMH. Boost engine: RD-268. Cruise Propulsion: Storable liquid rocket, N2O4/UDMH. Cruise engine: RD-862. Cruise Thrust: 142.627 kN (32,064 lbf). Guidance: Inertial. Total Number Built: 50.

  • Stage1: 1 x MR-UR-100 St 1. Gross Mass: 59,000 kg (130,000 lb). Empty Mass: 5,000 kg (11,000 lb). Motor: 1 x RD-268. Thrust (vac): 1,236.000 kN (277,863 lbf). Length: 14.30 m (46.90 ft). Diameter: 2.25 m (7.38 ft). Propellants: N2O4/UDMH.
  • Stage2: 1 x MR-UR-100-2. Gross Mass: 10,000 kg (22,000 lb). Empty Mass: 1,000 kg (2,200 lb). Motor: 1 x 15D169. Thrust (vac): 142.000 kN (31,922 lbf). Burn time: 195 sec. Length: 3.20 m (10.40 ft). Diameter: 2.15 m (7.05 ft). Propellants: N2O4/UDMH.
  • Stage3: 1 x MR-UR-100-3. Gross Mass: 1,000 kg (2,200 lb). Empty Mass: 500 kg (1,100 lb). Motor: 1 x MR-UR-100 BR. Length: 1.00 m (3.20 ft). Diameter: 2.15 m (7.05 ft). Propellants: N2O4/UDMH.
Version:

MR-UR-100U 15A16.
MR-UR-100
Credit - Ukrainian Space Agency
IOC: 1982. Other Designations: RS-16B. Department of Defence Designation: SS-17 Mod.3. ASCC Reporting Name: Spanker. Article Number: 15A16. Manufacturer's Designation: MR-UR-100U. Alternate Designation: MR-UR-100UTTKh. Launch System: 15P016. Missile: 15A16.

Development of the MR-UR-100UTTKh (UTTKh = 'Improved Technical-Tactical Characteristics) was authorised on 16 August 1976. The draft project was completed in December of the same year. The variant would use the super-hardened 15P715U universal silo, and have a modernised guidance system with better reliability and accuracy. Trials were conducted from 25 October 1977 to 15 December 1979. The missile was not formally accepted for military service until 1 December 1980. Between 1982 and 1984 the missile had entirely replaced the original MR-UR-100 in all 150 silos. Withdrawal of the missile began only four years later, the missile being replaced by the Topol mobile solid propellant ICBM at Bologoye and those at Kostroma being replaced by train-launched ICBM's. With the collapse of the Soviet Union the manufacturer ended up being in now-independent Ukraine - an unacceptable situation for a strategic weapon. By 1991 only 50 silos at Bologoye remained operational, and they were retired by 1994.

Launches: 23. Failures: 3. First Launch Date: 1977-10-25. Last Launch Date: 1981-04-18. Apogee: 1,000 km (600 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 71,100 kg (156,700 lb). Core Diameter: 2.25 m (7.38 ft). Total Length: 21.60 m (70.80 ft). Standard warhead mass: 2,550 kg (5,620 lb). Maximum range: 11,000 km (6,000 mi). Number Standard Warheads: 4. Standard warhead yield: 550 KT. Standard warhead CEP: 0.43 km (0.26 mi).

  • Stage1: 1 x MR-UR-100 St 1. Gross Mass: 59,000 kg (130,000 lb). Empty Mass: 5,000 kg (11,000 lb). Motor: 1 x RD-268. Thrust (vac): 1,236.000 kN (277,863 lbf). Length: 14.30 m (46.90 ft). Diameter: 2.25 m (7.38 ft). Propellants: N2O4/UDMH.
  • Stage2: 1 x MR-UR-100-2. Gross Mass: 10,000 kg (22,000 lb). Empty Mass: 1,000 kg (2,200 lb). Motor: 1 x 15D169. Thrust (vac): 142.000 kN (31,922 lbf). Burn time: 195 sec. Length: 3.20 m (10.40 ft). Diameter: 2.15 m (7.05 ft). Propellants: N2O4/UDMH.
  • Stage3: 1 x MR-UR-100-3. Gross Mass: 1,000 kg (2,200 lb). Empty Mass: 500 kg (1,100 lb). Motor: 1 x MR-UR-100 BR. Length: 1.00 m (3.20 ft). Diameter: 2.15 m (7.05 ft). Propellants: N2O4/UDMH.
Version:

Perimetr 15A11. Strategic communications missile. Article Number: 15A11. Alternate Designation: Perimeter. Complex: 15A11.

Perimetr was developed for launch of a highly secret communications payload. This would be be put in orbit or on a long high-altitude trajectory to provide back-up command and control of the strategic forces in the event of nuclear war.

A decree of 30 August 1974 authorised development under the supervision of Utkin at Yuzhnoye. The draft project for the new required factory test equipment was completed in December 1975, and that for the 15A11 rocket and its 15B99 payload in December 1977. Trials began in December 1979 and were completed in March 1982. The system entered service in January 1985 but was withdrawn by December 1990. The rocket was most likely based on Yuzhnoye's MR-UR-100, which would account for its rapid withdrawal from service after the collapse of the Soviet Union.

Launches: 11. Failures: 1. First Launch Date: 1979-01-01. Last Launch Date: 1988-01-01. Apogee: 1,000 km (600 mi). Liftoff Thrust: 1,236.000 kN (277,863 lbf). Total Mass: 71,000 kg (156,000 lb). Core Diameter: 2.25 m (7.38 ft). Total Length: 21.60 m (70.80 ft).

  • Stage1: 1 x Perimetr Stage 1. Gross Mass: 59,000 kg (130,000 lb). Empty Mass: 5,000 kg (11,000 lb). Motor: 1 x RD-268. Thrust (vac): 1,236.000 kN (277,863 lbf). Length: 14.90 m (48.80 ft). Diameter: 2.25 m (7.38 ft). Propellants: N2O4/UDMH.
  • Stage2: 1 x Perimetr 15A11-2. Gross Mass: 10,000 kg (22,000 lb). Empty Mass: 1,000 kg (2,200 lb). Motor: 1 x 15D169. Thrust (vac): 142.000 kN (31,922 lbf). Burn time: 195 sec. Length: 3.20 m (10.40 ft). Diameter: 2.15 m (7.05 ft). Propellants: Solid.
MR-UR-100 Chronology

1968 January 23 - Three-launch Soviet lunar expedition pitched Spacecraft: LK, Soyuz 7K-LOK, Soyuz 7K-L1, L3M-1970. The 'big' Soviet of Chief Designers meets and the three-launch landing concept developed a month earlier is presented in detail. Pilyugin pointed out that this was a typical contradiction. Mishin had just made a presentation to the expert commission justifying that the one-launch scheme was safe and reliable. Now they wanted to put forward a new scheme because the one-launch scheme was unsafe and unfeasible. Additional Details: Three-launch Soviet lunar expedition pitched.

1969 May 29 - N1 State Commission Spacecraft: LK, Soyuz 7K-L1A, Soyuz 7K-LOK, Aelita. Over two days a State Commission reviewed all of the conclusions of the N1 3L failure investigation and the readiness of N1 5L for flight. All of the fixes identified to remedy the 3L failure had been incorporated into 5L. It was felt that the behaviour of the systems in fire conditions were understood and appropriate measures had been taken. The wiring had been rerouted and insulated. Barmin wanted the system not to shut down any engines under any conditions during the first 15-20 seconds of flight, so that the booster would clear the pad and there would be no risk of the pad's destruction. But there was no time to develop such measures before the 5L launch; it could only be added in vehicle 6L. Additional Details: N1 State Commission.

1971 December 10 - Baikonur LC67/21. FAILURE: Failure. BI-2 Agency: RVSN. Apogee: 0 km ( mi).

1972 February 21 - Baikonur LC67/21. BI-2 Agency: RVSN. Apogee: 1.00 km (0.60 mi).

1972 March 21 - Baikonur LC67/21. BI-2 Agency: RVSN. Apogee: 1.00 km (0.60 mi).

1972 May 6 - Baikonur LC67/21. BI-3 Agency: RVSN. Apogee: 10 km (6 mi).

1972 May 24 - Baikonur LC67/21. BI-3 Agency: RVSN. Apogee: 10 km (6 mi).

1972 June 15 - Baikonur LC67/21. BI-3 Agency: RVSN. Apogee: 10 km (6 mi).

1972 September 15 - Baikonur LC173. BI-4 Agency: RVSN. Apogee: 1,000 km (600 mi).

1972 November 3 - Baikonur LC173. BI-4 Agency: RVSN. Apogee: 1,000 km (600 mi).

1972 December 22 - Baikonur LC67/21. BI-2 Agency: RVSN. Apogee: 1.00 km (0.60 mi).

1972 December 26 - Baikonur LC173. BI-4 Agency: RVSN. Apogee: 1,000 km (600 mi).

1973 March 12 - Baikonur LC173. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1973 April 6 - Baikonur LC177. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1973 June 5 - Baikonur LC173. FAILURE: Failure. State trials missile test Agency: RVSN. Apogee: 0 km ( mi).

1973 June 21 - Baikonur LC177. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1973 July 9 - Baikonur LC173. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1973 July 25 - Baikonur LC177. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1973 October 2 - Baikonur LC173. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1973 October 18 - Baikonur LC177. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1973 November 4 - Baikonur LC173. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1973 December 21 - Baikonur LC177. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1973 December 27 - Baikonur LC173. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 February 4 - Baikonur LC177. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 February 26 - Baikonur LC173. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 March 1 - Baikonur LC177. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 April 3 - Baikonur LC177. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 April 27 - Baikonur LC177. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 April 28 - Baikonur LC173. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 May 28 - Baikonur LC177. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 May 31 - Baikonur LC173. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 June 21 - Baikonur LC177. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 August 28 - Baikonur LC173. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 September 14 - Baikonur LC177. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 September 27 - Baikonur LC173. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 October 22 - Baikonur LC177. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 October 23 - Baikonur LC173. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 November 12 - Baikonur LC177. Operational test launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 December 17 - Baikonur LC177. Mod 2 state trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1975 April 23 - Baikonur LC173. Operational test launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1975 June 13 - Baikonur LC173. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1975 July 1 - Baikonur LC177. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1975 August 12 - Baikonur LC177. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1975 August 12 - Baikonur LC173. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 March 12 - Baikonur LC173. State trials flight Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 May 17 - Baikonur LC177. State trials flight Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 June 15 - Baikonur LC170. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 June 26 - Baikonur LC173. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 June 29 - Baikonur LC177. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 August 12 - Baikonur LC173. Operational test launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 October 21 - Baikonur LC170. FAILURE: Failure. Joint flight trials launch Agency: RVSN. Apogee: 0 km ( mi).

1976 October 26 - Baikonur LC177. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 December 14 - Baikonur LC170. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 December 16 - Baikonur LC173. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 December 30 - Baikonur LC177. FAILURE: Failure. Joint flight trials launch Agency: RVSN. Apogee: 0 km ( mi).

1977 March 26 - Baikonur LC173. Operational test launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1977 April 14 - Baikonur LC177. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1977 May 25 - Baikonur LC173. K? Agency: RVSN. Apogee: 1,000 km (600 mi).

1977 June 30 - Baikonur LC173. Operational test launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1977 July 30 - Baikonur LC177. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1977 October 25 - Baikonur LC177. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1977 December 29 - Baikonur LC177. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1978 February 27 - Baikonur LC177. Operational missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1978 March 26 - Baikonur LC173. Operational missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1978 March 31 - Baikonur LC177. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1978 April 27 - Baikonur LC170. FAILURE: Failure. Joint flight trials launch Agency: RVSN. Apogee: 0 km ( mi).

1978 June 5 - Baikonur LC173. Operational missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1978 June 5 - Baikonur LC177. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1978 June 28 - Baikonur LC170. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1978 August 11 - Baikonur LC173. Combat training launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1978 August 25 - Baikonur LC181. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1978 September 12 - Baikonur LC177. FAILURE: Failure. Joint flight trials launch Agency: RVSN. Apogee: 0 km ( mi).

1978 October 2 - Baikonur LC172. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1978 November 27 - Baikonur LC181. FAILURE: Failure. Joint flight trials launch Agency: RVSN. Apogee: 0 km ( mi).

1979 - Baikonur -. Perimetr 15A11 15B99 Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1979 May 21 - Baikonur LC170. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1979 May 31 - Baikonur -. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1979 June 26 - Baikonur -. SLI? Agency: RVSN. Apogee: 1,000 km (600 mi).

1979 June 29 - Baikonur LC170. Operational test Agency: RVSN. Apogee: 1,000 km (600 mi).

1979 July 20 - Baikonur LC172. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1979 August 2 - Baikonur LC170. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1979 August 3 - Baikonur LC181. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1979 August 30 - Baikonur LC170. SLI? Agency: RVSN. Apogee: 1,000 km (600 mi).

1979 September 14 - Baikonur -. SLI? Agency: RVSN. Apogee: 1,000 km (600 mi).

1979 November 15 - Baikonur -. Operational test Agency: RVSN. Apogee: 1,000 km (600 mi).

1979 December 26 - Baikonur LC181. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1980 - Baikonur -. Operational missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1980 March 6 - Baikonur LC172. Operational test Agency: RVSN. Apogee: 1,000 km (600 mi).

1981 - Baikonur -. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1981 April 18 - Baikonur LC172. Operational test Agency: RVSN. Apogee: 1,000 km (600 mi).

1982 - Baikonur -. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1982 - Baikonur -. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1982 - Baikonur -. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1982 - Baikonur -. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1982 January 28 - Baikonur -. FAILURE: Failure. Joint flight trials launch Agency: RVSN. Apogee: 0 km ( mi).

1983 - Baikonur -. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1984 - Baikonur -. Operational missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1984 - Baikonur -. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1984 November 13 - Baikonur -. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1988 - Baikonur -. Combat training launch Agency: RVSN. Apogee: 1,000 km (600 mi).

Bibliography:

  • McDowell, Jonathan, Jonathan's Space Home Page (launch records), Harvard University, 1997-present. Web Address when accessed: http://www.planet4589.org/jsr.html.
  • Pervov, Mikhail, Raketnoye Oruzhiye RVSN, Violanta, Moscow, 1999..
  • Karpenko, A V, Utkin, A F and Popov,A D, Otechestvenniye strategischeskiye raketnoye kompleks, Sankt-Peterburg: Nevskii bastion; Gangut 1999..
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MR-UR-100
Credit- © Mark Wade