UR-100N

UR-100N ICBM
Credit - © Mark Wade

Intercontinental ballistic missile. Year: 1974. IOC: 1974. Family: UR-100. Country: Russia. 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: 152. Failures: 18. Success Rate: 88.16%. First Launch Date: 1972-01-01. Last Launch Date: 2004-08-11. 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.

Model: Strela. Year: 1996. Family: UR-100. Country: Russia. Status: Out of production. 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.

Manufacturer: Chelomei. 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.

Model: UR-100NU. IOC: 1980. Family: UR-100. Country: Russia. Other Designations: RS-18B. Department of Defence Designation: SS-19 Mod 3. ASCC Reporting Name: Stilleto. Article Number: 15A35. Manufacturer's Designation: UR-100NU. Popular Name: Rokot. 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…

Manufacturer: Chelomei. 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.

Stage Data - UR-100N

Stage Number: 1. 1 x Stage: UR-100N Stage 1N. Gross Mass: 77,150 kg (170,080 lb). Empty Mass: 5,695 kg (12,555 lb). Thrust (vac): 1,778.661 kN (399,859 lbf). Isp: 310 sec. Burn time: 121 sec. Isp(sl): 285 sec. Diameter: 2.50 m (8.20 ft). Span: 2.50 m (8.20 ft). Length: 17.20 m (56.40 ft). Propellants: N2O4/UDMH. No Engines: 4. Engine: RD-0232.

Stage Number: 1. 1 x Stage: UR-100N Stage 1N. Gross Mass: 77,150 kg (170,080 lb). Empty Mass: 5,695 kg (12,555 lb). Thrust (vac): 1,778.661 kN (399,859 lbf). Isp: 310 sec. Burn time: 121 sec. Isp(sl): 285 sec. Diameter: 2.50 m (8.20 ft). Span: 2.50 m (8.20 ft). Length: 17.20 m (56.40 ft). Propellants: N2O4/UDMH. No Engines: 4. Engine: RD-0232.

Stage Number: 2. 1 x Stage: UR-100N Stage 2N. Gross Mass: 12,195 kg (26,885 lb). Empty Mass: 1,485 kg (3,273 lb). Thrust (vac): 214.270 kN (48,170 lbf). Isp: 322 sec. Burn time: 183 sec. Diameter: 2.50 m (8.20 ft). Span: 2.50 m (8.20 ft). Length: 3.90 m (12.70 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: RD-0235. Engine has one main engine and four verniers. Verniers continue to burn for 19 seconds after mainstage shutoff.

Stage Number: 2. 1 x Stage: UR-100N Stage 2N. Gross Mass: 12,195 kg (26,885 lb). Empty Mass: 1,485 kg (3,273 lb). Thrust (vac): 214.270 kN (48,170 lbf). Isp: 322 sec. Burn time: 183 sec. Diameter: 2.50 m (8.20 ft). Span: 2.50 m (8.20 ft). Length: 3.90 m (12.70 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: RD-0235. Engine has one main engine and four verniers. Verniers continue to burn for 19 seconds after mainstage shutoff.

Stage Number: 3. 1 x Stage: UR-100N MIRV Bus. Gross Mass: 1,100 kg (2,400 lb). Empty Mass: 725 kg (1,598 lb). Thrust (vac): 4.900 kN (1,102 lbf). Isp: 200 sec. Burn time: 150 sec. Diameter: 2.50 m (8.20 ft). Span: 2.50 m (8.20 ft). Length: 0.50 m (1.64 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: RD-0237.

UR-100N Chronology

1968 January 23 - Launch Vehicle: N1, UR-100N, MR-UR-100, RT-2.

Three-launch Soviet lunar expedition pitched Nation: USSR. Program: Lunar L3, Lunar L1. 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(51165). References: 367.

1969 May 29 - Launch Vehicle: N1, N1M, UR-700, N11, UR-100N, MR-UR-100, Proton 8K82K / 11S824.

N1 State Commission Nation: USSR. Program: Lunar L3. 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(51176). References: 367.

1972 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1972 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1973 April 9 - Launch Site: Baikonur. Launch Vehicle: UR-100N. FAILURE: Failure.

State trials missile test Nation: USSR. Agency: RVSN.

1973 Jun - Launch Site: Baikonur. Launch Vehicle: UR-100N.

State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1973 Jul - Launch Site: Baikonur. Launch Vehicle: UR-100N.

State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1973 Aug - Launch Site: Baikonur. Launch Vehicle: UR-100N.

State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1973 Sep - Launch Site: Baikonur. Launch Vehicle: UR-100N.

State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1973 Sep - Launch Site: Baikonur. Launch Vehicle: UR-100N.

State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1973 Oct - Launch Site: Baikonur. Launch Vehicle: UR-100N.

State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1973 Nov - Launch Site: Baikonur. Launch Vehicle: UR-100N.

State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1973 Dec - Launch Site: Baikonur. Launch Vehicle: UR-100N.

State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1973 Dec - Launch Site: Baikonur. Launch Vehicle: UR-100N.

State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 Jan 25? - Launch Site: Baikonur. Launch Vehicle: UR-100N.

State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 Jan 26? - Launch Site: Baikonur. Launch Vehicle: UR-100N.

State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 Feb 19? - Launch Site: Baikonur. Launch Vehicle: UR-100N.

State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 Feb 21? - Launch Site: Baikonur. Launch Vehicle: UR-100N.

State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 Jul - Launch Site: Baikonur. Launch Vehicle: UR-100N.

State trials missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1975 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

Joint flight trials launch Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1975 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

Operational missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1975 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

Operational missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1975 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

Joint flight trials launch Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1975 June 16 - Launch Site: Baikonur. Launch Vehicle: UR-100N. FAILURE: Failure.

Operational missile test Nation: USSR. Agency: RVSN.

1975 July 4 - Launch Site: Baikonur. Launch Vehicle: UR-100N. FAILURE: Failure.

Operational missile test Nation: USSR. Agency: RVSN.

1976 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

Operational missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 - Launch Site: Baikonur. Launch Vehicle: UR-100N. FAILURE: Failure.

Joint flight trials launch Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 - Launch Site: Baikonur. Launch Vehicle: UR-100N. FAILURE: Failure.

Joint flight trials launch Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

Operational missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

Operational missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

Operational missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

Operational missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

Operational missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

Joint flight trials launch Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

Joint flight trials launch Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 May 24 - Launch Site: Baikonur. Launch Vehicle: UR-100N. FAILURE: Failure.

Joint flight trials launch Nation: USSR. Agency: RVSN.

1976 August 21 - Launch Site: Baikonur. Launch Vehicle: UR-100N. FAILURE: Failure.

Joint flight trials launch Nation: USSR. Agency: RVSN.

1976 December 14 - Launch Site: Baikonur. Launch Vehicle: UR-100N. FAILURE: Failure.

Joint flight trials launch Nation: USSR. Agency: RVSN.

1976 December 28 - Launch Site: Baikonur. Launch Vehicle: UR-100N. FAILURE: Failure.

Joint flight trials launch Nation: USSR. Agency: RVSN.

1977 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

Operational missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1977 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

Operational missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1977 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

Operational missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1977 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

Operational missile test Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1977 - Launch Site: Baikonur. Launch Vehicle: UR-100N.

Joint flight trials launch Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1977 September 28 - Launch Vehicle: UR-100N. Model: UR-100NU.

First UR-100NU launch. Nation: USSR.

1977 October 26 - Launch Site: Baikonur. Launch Vehicle: UR-100N. Model: UR-100NU.

Joint flight trials launch Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi). References: 1445.

1977 Dec? - Launch Site: Baikonur. Launch Vehicle: UR-100N. Model: UR-100NU.

Joint flight trials launch Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).