UR-100N

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Intercontinental ballistic missile. IOC: 1974. Country: Russia. Status: Active. Other Designations: RS-18A. Department of Defence Designation: SS-19 Mod 1 and Mod 2. ASCC Reporting Name: Stilleto. Article Number: 15A30. Manufacturer's Designation: UR-100N. Popular Name: Rokot. Launch System: 15P030. Complex: 15A30.

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

Chief Designer Vladimir Chelomei began development of the UR-100N in 1967 as a replacement for his UR-100, the most widely deployed Soviet ICBM. He conceived of a modernised 8K84M capable of launching six independently-targeted nuclear warheads. Chief Designer Yangel at KB Yuzhnoye was promoting an alternate UR-100 replacement, his MR-UR-100. 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 as to which missile to put into production. Chelomei was supported by leadership figures Grechko, Afanasyev, and designers Sergeyev, Barmin, Baryshev and V Kuznetsov. The Yuzhnoye design was supported by Central Committee Secretary Ustinov, head of the VPK Military-Industrial Commission Smirnov, Mozhorin, Tyulin, and designers Glushko, and Pilyugin.

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.

Decrees authorising full development of the missile and silo were issued on 2 September 1969 and 19 August 1970. The missile was to feature a manoeuvrable post-boost bus for dispensing of warheads and countermeasures on different trajectories; a digital guidance system by V Sergeyev at NII-692; and shock mounting of the missile in the silo to improve survivability and the allow it to ride out an enemy counter-force nuclear attack. The rocket itself was increased in diameter to 2.41 m. The second stage engine was completely 'submerged' in the fuel tank, to allow the maximum missile mass to be packed into the existing UR-100 silos. This nearly tripled payload compared to the original UR-100. Baryshev at TsKBM Filial 2 designed the silo modifications. The new universal missile command point was designed by Krivoshein and Aksyutin at TsKB TM. The miniature nuclear warheads were the product of NII-1011 at Chelyabinsk-70.

Test flights began on 9 April 1973 at Baikonur. The last of 27 test launches were completed in October 1975. During the series tests were made with 1, 4, and 6 warhead configurations. The first regiment became active with the missile at Pervomaisk on 26 April 1975. The missile was formally accepted by the military on 30 December 1975. The first regiment with improved 'super-hardened' silos, able to resist overpressures of up to 450 atmospheres, became operational at Tatischevo on 18 December 1976. By 1979 240 missiles had been deployed. The INS, based on that developed for the R-36M by NPO Kharton, provided an 0.26 km CEP.

In service the missiles received a minor inspection and preventive maintenance visit every three months. A major inspection and maintenance is conducted every three years. The UR-100N was launched a total of 67 times by the year 2000. These included regular service launches to verify the missile's guaranteed life. In November 1994 a missile was launched successfully after 18 years in its storage container. A 10 June 1997 a twenty-year old missile, moved in its container from a silo in Kozelsk, was launched from Baikonur, followed by a 22 year old missile on 7 October 1998. These tests resulted in the missile being certified for 25 years life in 1999, which would allow field use of the UR-100N to 2010. There was every expectation that this could be extended to 30 years.

With the collapse of the Soviet Union, 130 UR-100N's at Khmelnitskiy and Pervomaisk had their warheads removed. The rockets themselves were returned to Russia between 29 August 1996 and February 1999. By September 1998 120 of the Ukrainian silos had been destroyed. The missile remained in service in 160 silos in Kozelsk (70) and Tatishchevo (90).

Manufacturer: Chelomei. Launches: 167. Failures: 15. Success Rate: 91.02%. First Launch Date: 1972-01-01. Last Launch Date: 2007-10-29. Launch data is: continuing. Apogee: 1,000 km (600 mi). Liftoff Thrust: 2,038.000 kN (458,160 lbf). Total Mass: 105,600 kg (232,800 lb). Core Diameter: 2.50 m (8.20 ft). Total Length: 24.00 m (78.00 ft). Span: 2.50 m (8.20 ft). Standard warhead mass: 4,350 kg (9,590 lb). Maximum range: 9,650 km (5,990 mi). Number Standard Warheads: 6. Standard warhead yield: 550 KT. Standard warhead CEP: 0.26 km (0.16 mi). Alternate warhead mass: 4,300 kg (9,400 lb). Maximum range with alternate warhead: 9,650 km (5,990 mi). Number Alternate Warheads: 1. Alternate warhead yield: 5,000 KT. Alternate warhead CEP: 0.26 km (0.16 mi). Boost Propulsion: Storable liquid rocket. Cruise Propulsion: Storable liquid rocket. Guidance: Inertial.

Stage1: 1 x UR-100N Stage 1N. Gross Mass: 77,150 kg (170,080 lb). Empty Mass: 5,695 kg (12,555 lb). Motor: 4 x RD-0232. Thrust (vac): 1,778.661 kN (399,859 lbf). Isp: 310 sec. Burn time: 121 sec. Length: 17.20 m (56.40 ft). Diameter: 2.50 m (8.20 ft). Propellants: N2O4/UDMH.

Stage2: 1 x UR-100N Stage 2N. Gross Mass: 12,195 kg (26,885 lb). Empty Mass: 1,485 kg (3,273 lb). Motor: 1 x RD-0235. Thrust (vac): 214.270 kN (48,170 lbf). Isp: 322 sec. Burn time: 183 sec. Length: 3.90 m (12.70 ft). Diameter: 2.50 m (8.20 ft). Propellants: N2O4/UDMH.

Version:

UR-100NU.
UR-100NU
Credit - Khrunichev
IOC: 1980. Status: Active. Other Designations: RS-18B. Department of Defence Designation: SS-19 Mod 3. ASCC Reporting Name: Stilleto. Article Number: 15A35. Manufacturer's Designation: UR-100NU. Alternate Designation: UR-100NUTTKh. Launch System: 15P035. Complex: 15A35.

Development of an improved version of the UR-100N was authorised on 16 April 1976 (UR-100NU; U = UTTKh = 'Improved Technical-Tactical Characteristics). Viktor Bugaisk at TsKBM headed the engineering team. The UR-100NU was to have a new warhead dispenser bus and improved guidance system by Vladimir Sergeyev of NII-692. The new system allowed up to six pre-programmed targets to be entered, any one of which could be selected at launch. This allowed deployment of better countermeasures and a considerable improvement in accuracy. A total of 68 test flights were conducted from 28 September 1977 to 26 July 1979. The missile was accepted for service on 17 December 1980. The first regiment was activated at Khmelnitskiy on 6 November 1979 and became operational in January 1981. By 1984 the UR-100NU had been placed in a total of 360 silos at Kozelsk (70), Pervomaisk (90), Khmelnitskiy (90) and Tatishchevo (110). Eventually all 360 silos were converted to the 'superhardened' standard. Production of the missile itself ended at Khrunichev in 1985 and this was the last ICBM built by the factory.

The silos at Kozelsk and Tatishchevo had been fitted with the final UR-100 series missile modification in 1988-1990 (under the SALT-2 treaty the number of warheads per missile was reduced from six to one). Tatishchevo was also the site of several service and exercise field launches. The purpose of these was to verify the guidance software's ballistic solution when fired from launch sites and impact zones other than the standard Baikonur/Kamchatka range. By 1999 the UR-100NU had been fired 81 times -- 27 trials launches, 25 operational exercises, and 29 for other purposes.

Surplus UR-100NU missiles were the subject of vigorous marketing as space launchers during the 1990's. Concepts promoted included:

Rokot, consisting of the UR-100NU plus a 'Briz' upper stage. This actually flew several times.
Okean, a sea-launched variant
Strela, using the basic UR-100NU as a space launcher
Prizyv, a global rapid rescue system proposed by NPO Mashinostroenniye and NIIMash. This envisioned SLA-1 and SLA-2 winged rescue flight vehicles to deliver supplies anywhere on earth within 15 to 180 minutes. The gliders would land 420 to 2500 kg of supplies anywhere on the planet to within 20 to 30 m of the aim point. This looked very much like a civilian version of Chelomei's 'Raketoplan' concept of the 1960's, focussed on attack on the US fleet. Perhaps it had remained on back-burner development all those years…

Launches: 79. Failures: 3. Success Rate: 96.20%. First Launch Date: 1977-09-28. Last Launch Date: 2007-10-29. Apogee: 1,000 km (600 mi). Liftoff Thrust: 1,870.000 kN (420,390 lbf). Total Mass: 105,600 kg (232,800 lb). Core Diameter: 2.50 m (8.20 ft). Total Length: 24.30 m (79.70 ft). Span: 2.50 m (8.20 ft). Standard warhead mass: 4,350 kg (9,590 lb). Maximum range: 10,000 km (6,000 mi). Number Standard Warheads: 6. Standard warhead yield: 550 KT. Standard warhead CEP: 0.31 km (0.19 mi). Boost Propulsion: Storable liquid rocket. Cruise Propulsion: Storable liquid rocket. Guidance: Inertial + Stellar.

Stage1: 1 x UR-100N Stage 1N. Gross Mass: 77,150 kg (170,080 lb). Empty Mass: 5,695 kg (12,555 lb). Motor: 4 x RD-0232. Thrust (vac): 1,778.661 kN (399,859 lbf). Isp: 310 sec. Burn time: 121 sec. Length: 17.20 m (56.40 ft). Diameter: 2.50 m (8.20 ft). Propellants: N2O4/UDMH.

Stage2: 1 x UR-100N Stage 2N. Gross Mass: 12,195 kg (26,885 lb). Empty Mass: 1,485 kg (3,273 lb). Motor: 1 x RD-0235. Thrust (vac): 214.270 kN (48,170 lbf). Isp: 322 sec. Burn time: 183 sec. Length: 3.90 m (12.70 ft). Diameter: 2.50 m (8.20 ft). Propellants: N2O4/UDMH.

Stage3: 1 x UR-100N MIRV Bus. Gross Mass: 1,100 kg (2,400 lb). Empty Mass: 725 kg (1,598 lb). Motor: 1 x RD-0237. Thrust (vac): 4.900 kN (1,102 lbf). Isp: 200 sec. Burn time: 150 sec. Length: 0.50 m (1.64 ft). Diameter: 2.50 m (8.20 ft). Propellants: N2O4/UDMH.

Version:

UR-100NU 15A35S.
Start Launcer
Status: Retired 1986.

Launches: 9. Failures: 2. First Launch Date: 1982-12-22. Last Launch Date: 1986-01-01. Apogee: 1,000 km (600 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 105,600 kg (232,800 lb). Core Diameter: 2.50 m (8.20 ft). Total Length: 24.30 m (79.70 ft). Maximum range: 10,000 km (6,000 mi).

Stage1: 1 x UR-100N Stage 1N. Gross Mass: 77,150 kg (170,080 lb). Empty Mass: 5,695 kg (12,555 lb). Motor: 4 x RD-0232. Thrust (vac): 1,778.661 kN (399,859 lbf). Isp: 310 sec. Burn time: 121 sec. Length: 17.20 m (56.40 ft). Diameter: 2.50 m (8.20 ft). Propellants: N2O4/UDMH.

Stage2: 1 x UR-100N Stage 2N. Gross Mass: 12,195 kg (26,885 lb). Empty Mass: 1,485 kg (3,273 lb). Motor: 1 x RD-0235. Thrust (vac): 214.270 kN (48,170 lbf). Isp: 322 sec. Burn time: 183 sec. Length: 3.90 m (12.70 ft). Diameter: 2.50 m (8.20 ft). Propellants: N2O4/UDMH.

Stage3: 1 x UR-100N MIRV Bus. Gross Mass: 1,100 kg (2,400 lb). Empty Mass: 725 kg (1,598 lb). Motor: 1 x RD-0237. Thrust (vac): 4.900 kN (1,102 lbf). Isp: 200 sec. Burn time: 150 sec. Length: 0.50 m (1.64 ft). Diameter: 2.50 m (8.20 ft). Propellants: N2O4/UDMH.

Version:

UR-100NU 15A35P.
Briz
Credit - Khrunichev
Status: Retired 1992.

Launches: 4. First Launch Date: 1990-03-29. Last Launch Date: 1992-07-28. Apogee: 1,000 km (600 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 105,600 kg (232,800 lb). Core Diameter: 2.50 m (8.20 ft). Total Length: 24.30 m (79.70 ft). Maximum range: 10,000 km (6,000 mi).

Stage1: 1 x UR-100N Stage 1N. Gross Mass: 77,150 kg (170,080 lb). Empty Mass: 5,695 kg (12,555 lb). Motor: 4 x RD-0232. Thrust (vac): 1,778.661 kN (399,859 lbf). Isp: 310 sec. Burn time: 121 sec. Length: 17.20 m (56.40 ft). Diameter: 2.50 m (8.20 ft). Propellants: N2O4/UDMH.

Stage2: 1 x UR-100N Stage 2N. Gross Mass: 12,195 kg (26,885 lb). Empty Mass: 1,485 kg (3,273 lb). Motor: 1 x RD-0235. Thrust (vac): 214.270 kN (48,170 lbf). Isp: 322 sec. Burn time: 183 sec. Length: 3.90 m (12.70 ft). Diameter: 2.50 m (8.20 ft). Propellants: N2O4/UDMH.

Stage3: 1 x UR-100N MIRV Bus. Gross Mass: 1,100 kg (2,400 lb). Empty Mass: 725 kg (1,598 lb). Motor: 1 x RD-0237. Thrust (vac): 4.900 kN (1,102 lbf). Isp: 200 sec. Burn time: 150 sec. Length: 0.50 m (1.64 ft). Diameter: 2.50 m (8.20 ft). Propellants: N2O4/UDMH.

Version:

Rokot.
Rokot
Credit - Khrunichev
All-solid orbital launch vehicle. Status: Active. Other Designations: RS-18. Department of Defence Designation: SS-19 Mod.1. Article Number: 15A30. Manufacturer's Designation: UR-100N.

Launch vehicle based decommissioned UR-100N ICBMs. 106 tonne liftoff mass with Briz-KM upper stage.

Launches: 11. Failures: 1. First Launch Date: 1990-11-20. Last Launch Date: 2006-07-28. LEO Payload: 1,800 kg (3,900 lb). to: 200 km Orbit. at: 53.00 degrees. Payload: 1,000 kg (2,200 lb). to a: sun synchronous, 800 km, 98.6 deg orbital trajectory. Associated Spacecraft: Cubesat, GRACE, LM 700, Monitor, Radio, SERVIS. Liftoff Thrust: 1,850.000 kN (415,890 lbf). Total Mass: 107,000 kg (235,000 lb). Core Diameter: 2.50 m (8.20 ft). Total Length: 29.10 m (95.40 ft). Launch Price $: 15.000 million. in: 1999 price dollars.

Stage1: 1 x UR-100N Stage 1N. Gross Mass: 77,150 kg (170,080 lb). Empty Mass: 5,695 kg (12,555 lb). Motor: 4 x RD-0232. Thrust (vac): 1,778.661 kN (399,859 lbf). Isp: 310 sec. Burn time: 121 sec. Length: 17.20 m (56.40 ft). Diameter: 2.50 m (8.20 ft). Propellants: N2O4/UDMH.

Stage2: 1 x UR-100N Stage 2N. Gross Mass: 12,195 kg (26,885 lb). Empty Mass: 1,485 kg (3,273 lb). Motor: 1 x RD-0235. Thrust (vac): 214.270 kN (48,170 lbf). Isp: 322 sec. Burn time: 183 sec. Length: 3.90 m (12.70 ft). Diameter: 2.50 m (8.20 ft). Propellants: N2O4/UDMH.

Stage3: 1 x Briz-KM. Gross Mass: 6,700 kg (14,700 lb). Empty Mass: 1,700 kg (3,700 lb). Motor: 1 x S5.98M. Thrust (vac): 19.600 kN (4,406 lbf). Burn time: 1,000 sec. Length: 2.50 m (8.20 ft). Diameter: 2.50 m (8.20 ft). Propellants: N2O4/UDMH.

Version:

Rokot K.
Rokot
All-solid orbital launch vehicle.

Version with Briz-K upper stage.

LEO Payload: 1,850 kg (4,070 lb). Apogee: 1,500 km (900 mi). Liftoff Thrust: 1,870.000 kN (420,390 lbf). Total Mass: 107,000 kg (235,000 lb). Core Diameter: 2.50 m (8.20 ft). Total Length: 29.00 m (95.00 ft).

Stage1: 1 x UR-100N Stage 1N. Gross Mass: 77,150 kg (170,080 lb). Empty Mass: 5,695 kg (12,555 lb). Motor: 4 x RD-0232. Thrust (vac): 1,778.661 kN (399,859 lbf). Isp: 310 sec. Burn time: 121 sec. Length: 17.20 m (56.40 ft). Diameter: 2.50 m (8.20 ft). Propellants: N2O4/UDMH.

Stage2: 1 x UR-100N Stage 2N. Gross Mass: 12,195 kg (26,885 lb). Empty Mass: 1,485 kg (3,273 lb). Motor: 1 x RD-0235. Thrust (vac): 214.270 kN (48,170 lbf). Isp: 322 sec. Burn time: 183 sec. Length: 3.90 m (12.70 ft). Diameter: 2.50 m (8.20 ft). Propellants: N2O4/UDMH.

Stage3: 1 x Rokot-3 Briz. Gross Mass: 6,565 kg (14,473 lb). Empty Mass: 1,600 kg (3,500 lb). Motor: 1 x S5.98M. Thrust (vac): 19.600 kN (4,406 lbf). Isp: 326 sec. Burn time: 1,000 sec. Length: 1.30 m (4.20 ft). Diameter: 2.50 m (8.20 ft). Propellants: N2O4/UDMH.

Version:

Strela.
Strela
Credit - © Mark Wade
Status: Active. Other Designations: RS-18. Department of Defence Designation: SS-19 Mod.1. Article Number: 15A30. Manufacturer's Designation: UR-100N.

Launch vehicle by NPO MASH based on UR-100N's decommissioned from Ukrainian missile fields. 106 tonne liftoff mass.

Launches: 1. First Launch Date: 2003-12-05. Last Launch Date: 2003-12-05. LEO Payload: 1,700 kg (3,700 lb). to: 200 km Orbit. at: 74.00 degrees. Liftoff Thrust: 1,900.000 kN (427,100 lbf). Total Mass: 104,000 kg (229,000 lb). Core Diameter: 2.50 m (8.20 ft). Total Length: 26.70 m (87.50 ft). Launch Price $: 10.500 million.

Stage1: 1 x UR-100N Stage 1N. Gross Mass: 77,150 kg (170,080 lb). Empty Mass: 5,695 kg (12,555 lb). Motor: 4 x RD-0232. Thrust (vac): 1,778.661 kN (399,859 lbf). Isp: 310 sec. Burn time: 121 sec. Length: 17.20 m (56.40 ft). Diameter: 2.50 m (8.20 ft). Propellants: N2O4/UDMH.

Stage2: 1 x UR-100N Stage 2N. Gross Mass: 12,195 kg (26,885 lb). Empty Mass: 1,485 kg (3,273 lb). Motor: 1 x RD-0235. Thrust (vac): 214.270 kN (48,170 lbf). Isp: 322 sec. Burn time: 183 sec. Length: 3.90 m (12.70 ft). Diameter: 2.50 m (8.20 ft). Propellants: N2O4/UDMH.

Stage3: 1 x Strela-3. Length: 1.30 m (4.20 ft). Diameter: 2.40 m (7.80 ft). Propellants: Solid.

UR-100N 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.

1972 - Baikonur -. FAILURE: Failure. Mod 1 state trials missile test Agency: RVSN. Apogee: 0 km ( mi).

1972 September 15 - Baikonur -. FAILURE: Failure. Mod 1 state trials missile test Agency: RVSN. Apogee: 0 km ( mi).

1973 April 9 - Baikonur -. Mod 2 state trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

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

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

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

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

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

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

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

1973 December 28 - Baikonur -. Mod 1 state trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

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

1974 January 25 - Baikonur -. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

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

1974 February 19 - Baikonur -. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

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

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

1975 - Baikonur -. Operational missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1975 - Baikonur -. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1975 June 16 - Baikonur -. FAILURE: Failure. Operational missile test Agency: RVSN. Apogee: 0 km ( mi).

1975 July 4 - Baikonur -. FAILURE: Failure. Operational missile test Agency: RVSN. Apogee: 0 km ( mi).

1976 - Baikonur -. Operational missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

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

1976 - Baikonur -. Operational missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

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

1976 - Baikonur -. Operational missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 - Baikonur -. SLI missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

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

1976 - Baikonur -. SLI missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 May 24 - Baikonur -. FAILURE: Failure. Joint flight trials launch Agency: RVSN. Apogee: 0 km ( mi).

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

1976 December 14 - Baikonur -. FAILURE: Failure. Joint flight trials launch Agency: RVSN. Apogee: 0 km ( mi).

1976 December 28 - Baikonur -. FAILURE: Failure. Joint flight trials launch Agency: RVSN. Apogee: 0 km ( mi).

1977 - Baikonur -. Operational missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

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

1977 September 28 - First UR-100NU launch.

1977 October 26 - Baikonur -. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

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

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

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

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

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

1979 - Baikonur -. 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).

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

1981 September 8 - Baikonur -. FAILURE: Failure. Joint flight trials launch Agency: RVSN. Apogee: 0 km ( mi).

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

1982 - Baikonur -. Operational missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1982 June 18 - Baikonur -. Operational missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1982 June 18 - Baikonur -. Combat training launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1982 December 22 - Baikonur -. FAILURE: Failure. SLI missile test Agency: RVSN. Apogee: 0 km ( mi).

1983 - Baikonur -. Operational missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

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

1983 - Baikonur -. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1983 September 2 - Baikonur -. FAILURE: Failure. Joint flight trials launch Agency: RVSN. Apogee: 0 km ( mi).

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

1984 December 6 - Baikonur -. FAILURE: Failure. Joint flight trials launch Agency: RVSN. Apogee: 0 km ( mi).

1985 - Baikonur -. Operational missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1986 - Baikonur -. Operational missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1986 - Baikonur -. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1987 - Baikonur -. Combat training launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1987 - Baikonur -. UBP Agency: RVSN. Apogee: 1,000 km (600 mi).

1987 February 12 - Tatishchevo -. Trajectory Test Agency: RVSN. Apogee: 1,000 km (600 mi).

1987 June 5 - Baikonur -. FAILURE: Failure. Combat training launch Agency: RVSN. Apogee: 0 km ( mi).

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

1990 February 28 - Baikonur -. Operational missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1990 March 29 - Baikonur -. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1990 November 20 - 04:00 GMT - Baikonur LC131. Rokot-K No. 1L Naryad-V Agency: VKS. Apogee: 900 km (550 mi). Noted as a suborbital test mission; but one Russian source indicates the payload was a Naryad-V satellite. That would indicate a failure to achieve orbit. No other information is available on the 'Naryad-V'.

1990 December 21 - Baikonur -. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1991 August 15 - 12:05 GMT - Baikonur -. Operational missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1991 November 26 - 02:30 GMT - Baikonur -. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1991 December 20 - 21:31 GMT - Baikonur LC175/2. Rokot-K No. 3L Grand Prix test Agency: VKS. Apogee: 1,000 km (600 mi).

1992 July 28 - Baikonur -. Joint flight trials launch Agency: RVSN RF. Apogee: 1,000 km (600 mi).

1992 December 1 - Baikonur -. FAILURE: Failure. Operational missile test Agency: RVSN RF. Apogee: 0 km ( mi).

1993 - Baikonur -. Operational missile test Agency: RVSN RF. Apogee: 1,000 km (600 mi).

1994 - Baikonur -. Operational missile test Agency: RVSN RF. Apogee: 1,000 km (600 mi).

1994 December 26 - 03:01 GMT - Baikonur LC175/59. Rokot-K No. 4L Radio-ROSTO RS-15 Mass: 70 kg (154 lb). Spacecraft: Radio. Agency: RKA. Perigee: 1,894 km (1,176 mi). Apogee: 2,151 km (1,336 mi). Inclination: 64.80 deg. Period: 127.70 min.

1995 June 8 - 12:45 GMT - Baikonur -. Operational missile test Agency: RVSN RF. Apogee: 1,000 km (600 mi).

1996 June 6 - Baikonur -. Operational test Agency: RVSN RF. Apogee: 1,000 km (600 mi).

1997 June 9 - Baikonur -. Operational missile test Agency: RVSN RF. Apogee: 1,000 km (600 mi).

1998 October 7 - 12:00 GMT - Baikonur -. Operational test Agency: RVSN RF. Apogee: 1,000 km (600 mi).

1998 December 10 - Baikonur -. Operational test Agency: RVSN RF. Apogee: 1,000 km (600 mi).

1999 October 20 - Baikonur LC175/2. Operational missile test Agency: RVSN RF. Apogee: 1,000 km (600 mi).

2000 May 16 - 08:27 GMT - Plesetsk LC133/1. Simsat-1 Mass: 657 kg (1,448 lb). Agency: Eurockot. Perigee: 543 km (337 mi). Apogee: 562 km (350 mi). Inclination: 86.37 deg. Period: 95.62 min. First Rokot flight from Plesetsk, using a launch pad originally used for Kosmos rockets. The two-stage modified UR-100NUTTKh ICBM, delivered a Briz-KM upper stage to a suborbital trajectory. The first Briz burn was to an approximately 200 x 550 km transfer orbit; the second burn circularized at apogee. It placed two 660 kg dummy satellites in orbits similar to the parking orbit was used for the defunct Iridium program. The Briz-KM stage then made a third burn to lower its perigee to a 178 x 556 km x 86.4 deg disposal orbit.

2000 November 1 - 10:00 GMT - Baikonur LC175/2. UR-100NU 15A35 87 Operational missile test Agency: RVSN RF. Apogee: 1,000 km (600 mi).

2001 June 27 - 04:35 GMT - Baikonur LC132. OT (KGCh-2?) operational test launch Agency: RVSN RF. Apogee: 1,000 km (600 mi).

2001 October 26 - 12:33 GMT - Baikonur LC175/2. Operational missile test Agency: RVSN RF. Apogee: 1,000 km (600 mi).

2002 March 17 - 09:21 GMT - Plesetsk LC133/1. GRACE 1 Mass: 432 kg (952 lb). Spacecraft: GRACE. Agency: DLR (Germany), NASA (U.S.). Perigee: 483 km (300 mi). Apogee: 506 km (314 mi). Inclination: 89.00 deg. First commercial flight of Rokot booster. Launch delayed from November 23-30, 2001, February 27, March 15 and 16. The Briz-KM upper stage ignited 5 minutes after launch and after a ten minute burn reached a 300 x 500 km orbit at about 0936 UTC. A second burn at 1042 UTC placed the satellites in a 483 x 506 km x 89 deg orbit; the two GRACE gravimetric satellites separated from the dispenser at 1047 UTC. A third Briz burn then lowered the rocket stage orbit to 146 x 487 km x 89 deg so that it would reenter quickly.

2002 June 20 - 09:33 GMT - Plesetsk LC133/3. Rokot 492882034 Iridium SV97 Mass: 690 kg (1,520 lb). Spacecraft: LM 700. Agency: Iridium. Perigee: 659 km (409 mi). Apogee: 669 km (415 mi). Inclination: 86.60 deg. Period: 98.00 min. Launch delayed from June 6, 19. The two Iridium replacement mobile telephone satellites were owned by Iridium Satellite LLC, the successor to bankrupt Iridium LLC.

2002 December 10 - 05:15 GMT - Baikonur LC132. OT 6RVs operational test launch Agency: RVSN RF. Apogee: 1,000 km (600 mi). Suborbital ICBM test with dummy warhead. Test delayed from November 1, December 5.

2003 June 30 - 14:14 GMT - Plesetsk LC133/3. Monitor-E/SL Mass: 700 kg (1,540 lb). Spacecraft: Monitor. Perigee: 694 km (431 mi). Apogee: 835 km (518 mi). Inclination: 98.70 deg. Period: 100.10 min. Delayed from October 2002, April 2003. Monitor-E mass model not released.

2003 October 30 - 13:43 GMT - Plesetsk LC133/3. Rokot 4921921121 Servis-1 Mass: 840 kg (1,850 lb). Spacecraft: SERVIS. Agency: USEF. Perigee: 984 km (611 mi). Apogee: 1,016 km (631 mi). Inclination: 99.50 deg. Period: 105.10 min. The mission of the 'Space Environment Reliability Verification of Integrated System' was to flight test a range of commerical-grade spacecraft components including a computer, star tracker, battery, and laser gyro. The objective was to lower the cost of future satellites.

2003 December 5 - 06:00 GMT - Baikonur LC175/2. Payload Mockup Perigee: 454 km (282 mi). Apogee: 460 km (280 mi). Inclination: 67.10 deg. Period: 93.70 min. Originally reported as an ICBM test. A Reuters story, later confirmed, claimed it was the first orbital launch of the Strela version of the rocket.

2004 February 18 - 09:00 GMT - Baikonur -. Operational missile test Agency: RVSN RF. Apogee: 1,000 km (600 mi). Launched during a nationwide military exercise.

2004 August 11 - 10:25 GMT - Baikonur -. Operational missile test Agency: RVSN RF. Apogee: 1,000 km (600 mi).

2005 August 26 - 18:34 GMT - Plesetsk LC133/3. Monitor-E Mass: 700 kg (1,540 lb). Spacecraft: Monitor. Agency: Roskosmos. Perigee: 522 km (324 mi). Apogee: 545 km (338 mi). Inclination: 97.50 deg. Period: 95.30 min. Delayed from June 30, July 30, August 18 2005. Prototype lightweight earth monitoring satellite with 8-meter and 20-meter resolution cameras.

2005 October 8 - 15:02 GMT - Plesetsk LC133/3. FAILURE: The first stage burned to depletion due to a missing command in the software sequence. This resulted in the second stage failing to separate. CryoSat Mass: 717 kg (1,580 lb). Spacecraft: CryoSat. Agency: ESA. ESA Earth Explorer 1 mission failed to orbit. The satellite was to have used radar altimetry for environmental survey of polar ice with great accuracy. Delayed from November 2004, March 25, June 24, July 11, September 15 and 27, 2005.

2005 October 20 - 07:30 GMT - Baikonur LC175/2. OT Kura Agency: RVSN RF. Apogee: 1,000 km (600 mi).

2006 July 28 - 07:05 GMT - Plesetsk LC133/3. Kompsat 2 Mass: 798 kg (1,759 lb). Spacecraft: KOMPSAT-2. Agency: KARI. Perigee: 676 km (420 mi). Apogee: 701 km (435 mi). Inclination: 98.10 deg. Period: 98.50 min. Carried a 1-meter-resolution Earth surveillance camera..

2006 November 9 - 11:35 GMT - Baikonur LC175/2. Operational missile test Agency: RVSN RF. Apogee: 1,000 km (600 mi).

2007 October 29 - 09:00 GMT - Baikonur LC175/2. Operational test Agency: RVSN RF. Apogee: 1,000 km (600 mi).

2008 May 23 - 15:20 GMT - Plesetsk . Yubileyniy Spacecraft: Strela-3. Perigee: 1,480 km (910 mi). Apogee: 1,508 km (937 mi). Inclination: 82.50 deg. Period: 115.80 min. Test satellite with an amateur radio payload to commemorate (belatedly) the 50th anniversary of Sputnik.

Bibliography:

McDowell, Jonathan, Jonathan's Space Home Page (launch records), Harvard University, 1997-present. Web Address when accessed: http://www.planet4589.org/jsr.html.
JPL Mission and Spacecraft Library, Jet Propulsion Laboratory, 1997. Web Address when accessed: http://msl.jpl.nasa.gov/home.html.
Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991 (succeeded by 2000 edition).
Placard, TsNIIMASH Museum,
Isakowitz, Steven J, Hopkins, Joshua B, and Hopkins, Joseph P, International Reference to Space Launch Systems, AIAA, Washington DC, 2004.
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..
NASA/GSFC Orbital Information Group Website, Web Address when accessed: http://oig1.gsfc.nasa.gov/.
Space-Launcher.com, Orbital Report News Agency. Web Address when accessed: http://www.orbireport.com/Log.html.

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© Mark Wade, 1997 - 2008 except where otherwise noted.

Universal Rockets
Credit- © Mark Wade
Chelomei's Universal Rocket Family. From left to right: UR-100 (three variants) and UR-100N (three variants). UR-200. Original UR-500 configuration, composed of clustered UR-200's. Conventional UR-500 monoblock configuration. Selected UR-500 polyblock configuration. UR-500 two-stage configuration - ICBM version and as flown. UR-500K configuration with LK-1; with Block D upper stage and L1; with Block D upper stage for satellite launch. UR-700.