R-39

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Submarine-launched ballistic missile. IOC: 1983. Country: Russia. Status: Active.

SLBM developed for use on Typhoon subs.

Manufacturer: Makeyev. Launches: 60. Failures: 3. Success Rate: 95.00%. First Launch Date: 1980-01-01. Last Launch Date: 2003-12-11. Launch data is: continuing. Version:

3M20.
R-39
IOC: 1983. Other Designations: RSM-52. Department of Defence Designation: SS-N-20 Mod 1. ASCC Reporting Name: Sturgeon. Article Number: 3R65. Popular Name: Rif-Ma. Launch System: D-19 Rif. Complex: 3R65. Missile: 3M20.

First flight 1979. Four unsuccessful tests in 1980, two successful in 1981. Development completed 1983. SLBM on Typhoon subs.

Total Mass: 81,000 kg (178,000 lb). Core Diameter: 2.40 m (7.80 ft). Total Length: 20.00 m (65.00 ft). Span: 2.40 m (7.80 ft). Standard warhead mass: 2,270 kg (5,000 lb). Maximum range: 8,400 km (5,200 mi). Number Standard Warheads: 10. Standard warhead yield: 100 KT. Standard warhead CEP: 0.50 km (0.31 mi). Boost Propulsion: Solid rocket. Cruise Propulsion: Solid rocket. Guidance: Inertial+Stellar. Total Number Built: 100. Version:

3M65. IOC: 1983. Other Designations: RSM-52. Department of Defence Designation: SS-N-20 Mod 2. ASCC Reporting Name: Sturgeon. Article Number: 3M65. Popular Name: Rif-Ma. Launch System: Taifun. Missile: 3M65.

First flight 1983. As of March 1986 only Russian SLBM in production.

Total Mass: 90,000 kg (198,000 lb). Core Diameter: 2.40 m (7.80 ft). Total Length: 15.98 m (52.42 ft). Span: 2.40 m (7.80 ft). Standard warhead mass: 2,270 kg (5,000 lb). Maximum range: 8,310 km (5,160 mi). Number Standard Warheads: 10. Standard warhead yield: 100 KT. Standard warhead CEP: 0.50 km (0.31 mi). Boost Propulsion: Solid rocket. Cruise Propulsion: Solid rocket. Guidance: Inertial+Stellar. Version:

Rif. Orbital launch vehicle. Status: Active.

R-39 SLBM adapted for use as suborbital test vehicle or orbital launch vehicle.

Manufacturer: Makeyev. Launches: 57. Success Rate: 100.00%. First Launch Date: 1980-01-01. Last Launch Date: 2003-12-11. Apogee: 1,000 km (600 mi). Liftoff Thrust: 2,060.000 kN (463,100 lbf). Total Mass: 84,000 kg (185,000 lb). Core Diameter: 2.40 m (7.80 ft). Total Length: 16.00 m (52.00 ft). Maximum range: 8,300 km (5,100 mi).

Stage1: 1 x R-39-1. Gross Mass: 53,700 kg (118,300 lb). Motor: 1 x 15D305. Thrust (vac): 2,060.000 kN (463,100 lbf). Length: 9.70 m (31.80 ft). Diameter: 2.40 m (7.80 ft). Propellants: Solid.

Stage2: 1 x Grom-2. Gross Mass: 25,000 kg (55,000 lb). Motor: 1 x R-39 St2. Length: 5.00 m (16.40 ft). Diameter: 2.40 m (7.80 ft). Propellants: N2O4/UDMH.

Stage3: 1 x Rif-3. Gross Mass: 10,000 kg (22,000 lb). Motor: 1 x R-39 St3. Length: 4.00 m (13.10 ft). Diameter: 2.40 m (7.80 ft). Propellants: N2O4/UDMH.

Version:

Rif-MA.
Rifma
Credit - © Mark Wade
Orbital launch vehicle. Status: Out of production. Other Designations: RSM-52. Department of Defence Designation: SS-N-20. Popular Name: Akvamarin.

Orbital launch vehicle derived from R-39 SLBM. Air-launched from An-124. Ignition mass 79 tonnes.

Manufacturer: Makeyev. LEO Payload: 1,500 kg (3,300 lb). to: 200 km Orbit. Payload: 950 kg (2,090 lb). to a: 700 km orbit trajectory. Version:

R-39M. Other Designations: RSM-52V. Department of Defence Designation: SS-N-28. Article Number: 3M91. Manufacturer's Designation: R-39M. Launch System: D-19UTH Grom. Missile: 3M91.

Improved version.

Version:

Grom. Orbital launch vehicle. Status: Retired 1997.

Three stage vehicle consisting of 1 x R-39 St 1 + 1 x R-39 St 2 + 1 x R-39 St 3

Manufacturer: Makeyev. Launches: 3. Failures: 3. First Launch Date: 1996-01-01. Last Launch Date: 1997-11-19. Apogee: 1,000 km (600 mi). Liftoff Thrust: 2,060.000 kN (463,100 lbf). Total Mass: 84,000 kg (185,000 lb). Core Diameter: 2.40 m (7.80 ft). Total Length: 16.00 m (52.00 ft). Maximum range: 8,300 km (5,100 mi).

Stage1: 1 x R-39-1. Gross Mass: 53,700 kg (118,300 lb). Motor: 1 x 15D305. Thrust (vac): 2,060.000 kN (463,100 lbf). Length: 9.70 m (31.80 ft). Diameter: 2.40 m (7.80 ft). Propellants: Solid.

Stage2: 1 x Grom-2. Gross Mass: 25,000 kg (55,000 lb). Motor: 1 x R-39 St2. Length: 5.00 m (16.40 ft). Diameter: 2.40 m (7.80 ft). Propellants: N2O4/UDMH.

Stage3: 1 x Rif-3. Gross Mass: 10,000 kg (22,000 lb). Motor: 1 x R-39 St3. Length: 4.00 m (13.10 ft). Diameter: 2.40 m (7.80 ft). Propellants: N2O4/UDMH.

Version:

R-39UTTKh. Other Designations: RSM-52M. Department of Defence Designation: SS-N-28. Article Number: 3M91. Manufacturer's Designation: R-39UTTKh. Missile: 3M91.

Version:

Priboy/Surf.
Priboy
Credit - © Mark Wade
Orbital launch vehicle. Status: Design 1993.

Launch vehicle using the 1st stage of the SS-N-20 SLBM topped by an SS-N-23 SLBM (RSM-52+RSM-54). Liftoff mass 104 tonnes. Can be launched from stationary or mobile platforms.

Manufacturer: Makeyev. LEO Payload: 2,400 kg (5,200 lb). to: 200 km Orbit.

R-39 Chronology

1980 January 1 - Nenoksa -. Test mission Agency: RVSN. Apogee: 1,000 km (600 mi).

1981 December 1 - Nenoksa -. Test mission Agency: RVSN. Apogee: 1,000 km (600 mi).

1982 October 14 - White Sea Launch Area -. Test mission Agency: RVSN. Apogee: 1,000 km (600 mi). Launched from White Sea Launch Area, Beloye More, Archangel'sk Oblast' - Latitude: 65.50 N - Longitude: 38.00 E.

1982 October 14 - White Sea Launch Area -. Silo Test launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1983 - Sea-launched -. Test mission Agency: RVSN. Apogee: 1,000 km (600 mi).

1995 August 25 - Arctic Ocean -. Test mission Agency: VMF. Apogee: 1,000 km (600 mi).

1996 - Nenoksa -. FAILURE: Failure. Test mission Agency: RVSN/VMF. Apogee: 0 km ( mi).

1996 October 23 - Barents Sea Launch Area -. Arms control Agency: VMF. Apogee: 3.00 km (1.80 mi).

1997? - Nenoksa -. FAILURE: Failure. Test mission Agency: RVSN/VMF. Apogee: 0 km ( mi).

1997 March 27 - Barents Sea Launch Area -. Arms control Agency: VMF. Apogee: 3.00 km (1.80 mi).

1997 March 28 - Barents Sea Launch Area -. Arms control Agency: VMF. Apogee: 3.00 km (1.80 mi).

1997 November 19 - Nenoksa -. FAILURE: Failure. Test mission Agency: RVSN/VMF. Apogee: 0 km ( mi).

1997 December 3 - Barents Sea Launch Area -. Arms control Agency: VMF. Apogee: 10 km (6 mi).

1997 December 4 - Barents Sea Launch Area -. Arms control Agency: VMF. Apogee: 10 km (6 mi).

1999 November 17 - Barents Sea Launch Area -. Test mission Agency: RVSN. Apogee: 1,000 km (600 mi).

2003 December 11 - White Sea Launch Area -. RSM-52M / R-39UTTKh / Grom test Agency: RVSN. Apogee: 1,000 km (600 mi). Launched from White Sea Launch Area, Beloye More, Archangel'sk Oblast' - Latitude: 65.50 N - Longitude: 38.00 E.

Bibliography:

McDowell, Jonathan, Jonathan's Space Home Page (launch records), Harvard University, 1997-present. Web Address when accessed: http://www.planet4589.org/jsr.html.
Placard, TsNIIMASH Museum,

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

ICBM-Derived LVs
Credit- © Mark Wade
The range of launch vehicles derived from decommissioned ballistic missiles offered for sale by Russia after the cold war.