R-29

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Submarine-launched ballistic missile. IOC: 1973. Country: Russia. Status: Active. Other Designations: RSM-40. Department of Defence Designation: SS-N-8 Mod 1. ASCC Reporting Name: Sawfly. Article Number: 4K75. Manufacturer's Designation: R-29. Popular Name: Vysota. Launch System: D-8. Complex: 4K75.

First intercontinental submarine-launched ballistic missile (range 7800 km). First flight 1969. Development completed 1973. The variants of this missile were given three different DoD designations over the years (SS-N-8, SS-N-18, and SS-N-23).

Manufacturer: Makeyev. Launches: 94. Failures: 3. Success Rate: 96.81%. First Launch Date: 1969-03-01. Last Launch Date: 2007-12-25. Launch data is: continuing. Associated Spacecraft: Tubsat. Total Mass: 32,800 kg (72,300 lb). Core Diameter: 1.80 m (5.90 ft). Total Length: 13.20 m (43.30 ft). Span: 1.80 m (5.90 ft). Standard warhead mass: 680 kg (1,490 lb). Maximum range: 7,700 km (4,700 mi). Number Standard Warheads: 1. Standard warhead yield: 1,000 KT. Standard warhead CEP: 1.56 km (0.96 mi). Boost Propulsion: Storable liquid rocket. Cruise Propulsion: Storable liquid rocket. Guidance: Inertial+Stellar. Version:

R-29R.
R-29R
IOC: 1979. Other Designations: RSM-50. Department of Defence Designation: SS-N-18 Mod 1. ASCC Reporting Name: Stingray. Article Number: 4K75DU. Manufacturer's Designation: R-29R. Popular Name: Volna. Alternate Designation: R-29R-2S. Launch System: D-9. Complex: 4K75DU. Missile: 3M40.

First flight 1975; Nov 1978 first sub launch. Developed 1973-1977. 3 MIRV

Manufacturer: Makayev. Total Mass: 34,388 kg (75,812 lb). Core Diameter: 1.80 m (5.90 ft). Total Length: 14.40 m (47.20 ft). Span: 1.80 m (5.90 ft). Standard warhead mass: 1,300 kg (2,800 lb). Maximum range: 6,500 km (4,000 mi). Number Standard Warheads: 3. Standard warhead yield: 200 KT. Standard warhead CEP: 1.40 km (0.80 mi). Boost Propulsion: Storable liquid rocket. Cruise Propulsion: Storable liquid rocket. Guidance: Inertial. Version:

R-29D.
R-29
IOC: 1977. Other Designations: RSM-40. Department of Defence Designation: SS-N-8 Mod 2. ASCC Reporting Name: Sawfly. Article Number: 4K75D. Manufacturer's Designation: R-29D. Popular Name: Vysota. Launch System: D-8.

First flight 1976. Development completed 1974 according to Makeyev.

Total Mass: 33,300 kg (73,400 lb). Core Diameter: 1.80 m (5.90 ft). Total Length: 13.00 m (42.00 ft). Span: 1.80 m (5.90 ft). Standard warhead mass: 860 kg (1,890 lb). Maximum range: 9,100 km (5,600 mi). Number Standard Warheads: 1. Standard warhead yield: 800 KT. Standard warhead CEP: 0.97 km (0.60 mi). Boost Propulsion: Storable liquid rocket. Cruise Propulsion: Storable liquid rocket. Guidance: Inertial+Stellar. Version:

R-29K. IOC: 1978. Other Designations: RSM-50. Department of Defence Designation: SS-N-18 Mod 2. ASCC Reporting Name: Stingray. Article Number: 4K75K. Manufacturer's Designation: R-29K. Popular Name: Volna. Launch System: D-9. Complex: 4K75K.

First flight 1977.

Manufacturer: Makayev. Total Mass: 34,388 kg (75,812 lb). Core Diameter: 1.80 m (5.90 ft). Total Length: 14.40 m (47.20 ft). Span: 1.80 m (5.90 ft). Standard warhead mass: 820 kg (1,800 lb). Maximum range: 7,980 km (4,950 mi). Number Standard Warheads: 1. Standard warhead yield: 450 KT. Standard warhead CEP: 0.90 km (0.55 mi). Boost Propulsion: Storable liquid rocket. Cruise Propulsion: Storable liquid rocket. Guidance: Inertial. Version:

R-29RL. IOC: 1981. Other Designations: RSM-50. Department of Defence Designation: SS-N-18 Mod 3. ASCC Reporting Name: Stingray. Article Number: 4K75R. Manufacturer's Designation: R-29RL. Popular Name: Volna. Launch System: D-9. Complex: 4K75R. Missile: 3M65.

First flight 1981. SLBM on Delta 2 subs. 7 MIRV

Manufacturer: Makayev. Total Mass: 35,300 kg (77,800 lb). Core Diameter: 1.80 m (5.90 ft). Total Length: 14.09 m (46.21 ft). Span: 1.80 m (5.90 ft). Standard warhead mass: 1,300 kg (2,800 lb). Maximum range: 6,500 km (4,000 mi). Number Standard Warheads: 7. Standard warhead yield: 200 KT. Standard warhead CEP: 0.90 km (0.55 mi). Boost Propulsion: Storable liquid rocket. Cruise Propulsion: Storable liquid rocket. Guidance: Inertial + Stellar. Version:

R-29RM.
R-29RM
IOC: 1988. Status: Active. Other Designations: RSM-54. Department of Defence Designation: SS-N-23. ASCC Reporting Name: Skif. Article Number: 4K75RM. Manufacturer's Designation: R-29RM. Popular Name: Shtil. Launch System: D-9RM Shtil. Complex: 4K75RM. Missile: 3M37.

SLBM on Delta 4 subs. First flight June 1983. Developed 1973-1986.

Launches: 1. First Launch Date: 2003-10-15. Last Launch Date: 2003-10-15. Total Mass: 40,300 kg (88,800 lb). Core Diameter: 1.90 m (6.20 ft). Total Length: 14.80 m (48.50 ft). Span: 1.90 m (6.20 ft). Standard warhead mass: 1,810 kg (3,990 lb). Maximum range: 8,310 km (5,160 mi). Number Standard Warheads: 10. Standard warhead yield: 100 KT. Standard warhead CEP: 0.90 km (0.55 mi). Boost Propulsion: Storable liquid rocket. Cruise Propulsion: Storable liquid rocket. Stage 3 Propellants: Storable liquid rocket. Guidance: Inertial + Stellar. Total Number Built: 64. Version:

Volna SLV.
Volna
Credit - © Mark Wade
Intercontinental ballistic orbital launch vehicle. Status: Out of production. Other Designations: RSM-50. Department of Defence Designation: SS-N-18.

Launch vehicle based on R-29RL SLBM. Suborbital, orbital versions. Payload volume 1.3 cu. m. Payload 115 kg to 3000 km or 1250 kg to 200 km. Liftoff mass 34 tonnes.

LEO Payload: 120 kg (260 lb). to: 200 km Orbit. Apogee: 1,000 km (600 mi). Liftoff Thrust: 682.000 kN (153,319 lbf). Total Mass: 35,300 kg (77,800 lb). Core Diameter: 1.90 m (6.20 ft). Total Length: 14.10 m (46.20 ft). Maximum range: 6,500 km (4,000 mi).

Stage1: 1 x Volna-1. Gross Mass: 20,000 kg (44,000 lb). Motor: 1 x RD R-29R (1). Thrust (vac): 682.000 kN (153,319 lbf). Burn time: 74 sec. Length: 7.70 m (25.20 ft). Diameter: 1.90 m (6.20 ft). Propellants: N2O4/UDMH.

Stage2: 1 x Volna-2. Gross Mass: 10,000 kg (22,000 lb). Motor: 1 x RD R-29R (2). Length: 3.10 m (10.10 ft). Diameter: 1.80 m (5.90 ft). Propellants: N2O4/UDMH.

Version:

Vysota.
Vysota
Credit - © Mark Wade
Intercontinental ballistic suborbital launch vehicle. Status: Retired 1996. Other Designations: RSM-40. Department of Defence Designation: SS-N-8.

Two stage vehicle based on R-29D SLBM. Suborbital; 30-55 min zero G. Payload volume 0.7 cu. m. Payload 115 kg to 5200 km or 1150 kg to 200 km. Liftoff mass 33 tonnes.

Launches: 30. Success Rate: 100.00%. First Launch Date: 1969-03-01. Last Launch Date: 1996-07-15. LEO Payload: 120 kg (260 lb). to: 200 km Orbit. Apogee: 1,000 km (600 mi). Liftoff Thrust: 682.000 kN (153,319 lbf). Total Mass: 33,300 kg (73,400 lb). Core Diameter: 1.90 m (6.20 ft). Total Length: 13.00 m (42.00 ft). Maximum range: 9,100 km (5,600 mi).

Stage1: 1 x Vysota-1. Gross Mass: 20,000 kg (44,000 lb). Motor: 1 x RD R-29 (1). Thrust (vac): 682.000 kN (153,319 lbf). Burn time: 74 sec. Length: 7.70 m (25.20 ft). Diameter: 1.90 m (6.20 ft). Propellants: N2O4/UDMH.

Stage2: 1 x Vysota-2. Gross Mass: 10,000 kg (22,000 lb). Motor: 1 x RD R-29 (2). Length: 3.10 m (10.10 ft). Diameter: 1.80 m (5.90 ft). Propellants: N2O4/UDMH.

Version:

Shtil.
ICBM-Derived LVs
Credit - © Mark Wade
Intercontinental ballistic orbital launch vehicle. Status: Active.

Three stage vehicle based on R-29RM SLBM.

Launches: 20. First Launch Date: 1983-06-01. Last Launch Date: 2004-09-08. Apogee: 1,000 km (600 mi). Liftoff Thrust: 682.000 kN (153,319 lbf). Total Mass: 40,300 kg (88,800 lb). Core Diameter: 1.90 m (6.20 ft). Total Length: 14.80 m (48.50 ft). Maximum range: 8,300 km (5,100 mi).

Stage1: 1 x R-29-1. Gross Mass: 20,000 kg (44,000 lb). Motor: 1 x RD-0244. Thrust (vac): 682.000 kN (153,319 lbf). Burn time: 74 sec. Length: 7.70 m (25.20 ft). Diameter: 1.90 m (6.20 ft). Propellants: N2O4/UDMH.

Stage2: 1 x Shtil'-2. Gross Mass: 10,000 kg (22,000 lb). Motor: 1 x RD R-29RM (2). Length: 4.90 m (16.00 ft). Diameter: 1.90 m (6.20 ft). Propellants: N2O4/UDMH.

Stage3: 1 x Shtil'-1-3. Gross Mass: 10,000 kg (22,000 lb). Motor: 1 x RD R-29RM (3). Length: 2.80 m (9.10 ft). Diameter: 1.90 m (6.20 ft). Propellants: N2O4/UDMH.

Version:

Shtil-1/1N. Intercontinental ballistic orbital launch vehicle. Status: Active. Other Designations: RSM-54. Department of Defence Designation: SS-N-23.

Three stage vehicle based on R-29RM SLBM.

Launches: 2. First Launch Date: 1998-07-07. Last Launch Date: 2006-05-26. LEO Payload: 430 kg (940 lb). to: 200 km Orbit. Payload: 185 kg (407 lb). to a: 700 km orbit trajectory. Apogee: 1,000 km (600 mi). Liftoff Thrust: 809.000 kN (181,870 lbf). Total Mass: 40,000 kg (88,000 lb). Core Diameter: 1.90 m (6.20 ft). Total Length: 14.80 m (48.50 ft). Launch Price $: 0.500 million. in: 1999 price dollars.

Stage1: 1 x R-29-1. Gross Mass: 20,000 kg (44,000 lb). Motor: 1 x RD-0244. Thrust (vac): 682.000 kN (153,319 lbf). Burn time: 74 sec. Length: 7.70 m (25.20 ft). Diameter: 1.90 m (6.20 ft). Propellants: N2O4/UDMH.

Stage2: 1 x Shtil'-2. Gross Mass: 10,000 kg (22,000 lb). Motor: 1 x RD R-29RM (2). Length: 4.90 m (16.00 ft). Diameter: 1.90 m (6.20 ft). Propellants: N2O4/UDMH.

Stage3: 1 x Shtil'-1-3. Gross Mass: 10,000 kg (22,000 lb). Motor: 1 x RD R-29RM (3). Length: 2.80 m (9.10 ft). Diameter: 1.90 m (6.20 ft). Propellants: N2O4/UDMH.

Version:

Shtil-2/2N.
Shtil-2
Credit - © Mark Wade
Intercontinental ballistic orbital launch vehicle. Status: Out of production. Other Designations: RSM-54. Department of Defence Designation: SS-N-23.

Three stage vehicle based on R-29RM SLBM with a special shroud. Liftoff mass 40 tonnes. Stationary launch platform.

LEO Payload: 350 kg (770 lb). to: 200 km Orbit. Payload: 70 kg (154 lb). to a: 700 km orbit trajectory. Liftoff Thrust: 809.000 kN (181,870 lbf). Total Mass: 40,000 kg (88,000 lb). Total Length: 18.40 m (60.30 ft). Launch Price $: 0.500 million. in: 1999 price dollars. Version:

Shtil-3A.
Shtil-3A
Credit - © Mark Wade
Intercontinental ballistic orbital launch vehicle. Status: Out of production. Other Designations: RSM-54. Library of Congress Designation: SS-N-23. Popular Name: Aerokosmos.

Proposed four-stage air-launched orbital launch vehicle based on R-29RM SLBM. Ignition mass 46 tonnes.

LEO Payload: 950 kg (2,090 lb). to: 200 km Orbit. Payload: 620 kg (1,360 lb). to a: 400 km orbit trajectory. Total Mass: 46,000 kg (101,000 lb). Version:

Shtil-3N. Status: Out of production. Other Designations: RSM-54. Department of Defence Designation: SS-N-23.

Proposed orbital launch vehicle based on R-29RM SLBM with new third and additional fourth stages. Stationary launch. Liftoff mass 46 tonnes.

LEO Payload: 410 kg (900 lb). to: 200 km Orbit. Payload: 220 kg (480 lb). to a: 700 km orbit trajectory. Total Mass: 46,000 kg (101,000 lb). Version:

Sineva. Status: Active.

Manufacturer: Makeyev. Launches: 9. Failures: 1. First Launch Date: 2004-02-18. Last Launch Date: 2007-12-25. Apogee: 1,000 km (600 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 40,300 kg (88,800 lb). Core Diameter: 1.90 m (6.20 ft). Total Length: 14.80 m (48.50 ft). Maximum range: 8,300 km (5,100 mi).

Stage1: 1 x R-29-1. Gross Mass: 20,000 kg (44,000 lb). Motor: 1 x RD-0244. Thrust (vac): 682.000 kN (153,319 lbf). Burn time: 74 sec. Length: 7.70 m (25.20 ft). Diameter: 1.90 m (6.20 ft). Propellants: N2O4/UDMH.

Stage2: 1 x Shtil'-2. Gross Mass: 10,000 kg (22,000 lb). Motor: 1 x RD R-29RM (2). Length: 4.90 m (16.00 ft). Diameter: 1.90 m (6.20 ft). Propellants: N2O4/UDMH.

Stage3: 1 x Shtil'-1-3. Gross Mass: 10,000 kg (22,000 lb). Motor: 1 x RD R-29RM (3). Length: 2.80 m (9.10 ft). Diameter: 1.90 m (6.20 ft). Propellants: N2O4/UDMH.

R-29 Chronology

1969 March 1 - Nenoksa -. Test mission Agency: VMF. Apogee: 1,000 km (600 mi).

1969 June 21 - Nenoksa -. Test mission Agency: VMF. Apogee: 1,000 km (600 mi).

1970 - Nenoksa -. Test mission Agency: VMF. Apogee: 1,000 km (600 mi).

1971 - Nenoksa -. Test mission Agency: VMF. Apogee: 1,000 km (600 mi).

1971 December 15 - White Sea Launch Area -. Test mission Agency: VMF. Apogee: 1,000 km (600 mi).

1972 August 1 - White Sea Launch Area -. Test mission Agency: VMF. 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.

1972 September 1 - White Sea Launch Area -. Test mission Agency: VMF. 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.

1972 October 1 - White Sea Launch Area -. Test mission Agency: VMF. 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.

1972 November 25 - White Sea Launch Area -. Test mission Agency: VMF. 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.

1972 November 28 - White Sea Launch Area -. Test mission Agency: VMF. 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.

1972 December 14 - White Sea Launch Area -. Test mission Agency: VMF. 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.

1974 February 1 - Nenoksa -. Test mission Agency: VMF. Apogee: 1,000 km (600 mi).

1974 September 1 - Nenoksa -. Test mission Agency: VMF. Apogee: 1,000 km (600 mi).

1975 - Nenoksa -. Volna VMF Test mission Agency: VMF. Apogee: 1,000 km (600 mi).

1976 - Nenoksa -. Operational test Agency: VMF. Apogee: 1,000 km (600 mi).

1976 November 1 - White Sea Launch Area -. Volna VMF Test mission Agency: VMF. 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.

1977 Q1 - Sea-launched -. Volna VMF Test mission Agency: VMF. Apogee: 1,000 km (600 mi).

1977 March 18 - Barents Sea Launch Area -. Test mission Agency: VMF. Apogee: 1,000 km (600 mi).

1977 March 20 - Barents Sea Launch Area -. Test mission Agency: VMF. Apogee: 1,000 km (600 mi).

1977 November 1 - Sea-launched -. Volna VMF Test mission Agency: VMF. Apogee: 1,000 km (600 mi).

1977 December 1 - Sea-launched -. Volna VMF Test mission Agency: VMF. Apogee: 1,000 km (600 mi).

1978 September 1 - Sea-launched -. Volna VMF Test mission Agency: VMF. Apogee: 1,000 km (600 mi).

1980 - White Sea Launch Area -. Volna VMF Test mission Agency: VMF. 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.

1981 - Okhotsk -. Operational test Agency: VMF. Apogee: 1,000 km (600 mi).

1981 - Okhotsk -. Volna VMF Operational test Agency: VMF. Apogee: 1,000 km (600 mi).

1981 - Okhotsk -. Operational test Agency: VMF. Apogee: 1,000 km (600 mi).

1981 - Okhotsk -. Volna VMF Operational test Agency: VMF. Apogee: 1,000 km (600 mi).

1981 - Okhotsk -. Operational test Agency: VMF. Apogee: 1,000 km (600 mi).

1983 June 1 - Nenoksa -. Shtil VMF State trials missile test Agency: VMF. Apogee: 1,000 km (600 mi).

1986 September 1 - Barents Sea Launch Area -. Test mission Agency: VMF. Apogee: 1,000 km (600 mi).

1991 December 1 - Sea-launched -. Volna VMF Operational test Agency: VMF. Apogee: 1,000 km (600 mi).

1992 - Sea-launched -. Volna VMF RF Operational test Agency: VMF RF. Apogee: 1,000 km (600 mi).

1993 December 1 - Sea-launched -. Volna VMF RF Operational test Agency: VMF RF. Apogee: 1,000 km (600 mi).

1995 June 6 - 22:10 GMT - Barents Sea Launch Area -. Volna VMF RF Volan? Agency: VMF RF. Apogee: 1,270 km (780 mi).

1996 June 28 - Okhotsk -. Operational test Agency: VMF RF. Apogee: 1,000 km (600 mi).

1996 July 15 - Barents Sea Launch Area -. Operational test Agency: VMF RF. Apogee: 1,000 km (600 mi).

1996 October 3 - Barents Sea Launch Area -. Operational test Agency: VMF RF. Apogee: 1,000 km (600 mi).

1997 January 15 - Barents Sea Launch Area -. Operational test Agency: VMF RF. Apogee: 1,000 km (600 mi).

1997 July 23 - Okhotsk -. Operational test Agency: VMF RF. Apogee: 1,000 km (600 mi).

1998 February 19 - Barents Sea Launch Area -. Operational test Agency: VMF RF. Apogee: 1,000 km (600 mi).

1998 July 7 - 03:15 GMT - Barents Sea Launch Area -. Tubsat-N Mass: 8.00 kg (17.60 lb). Spacecraft: Tubsat. Agency: TUB. Perigee: 400 km (240 mi). Apogee: 776 km (482 mi). Inclination: 78.90 deg. Period: 96.40 min. The first satellite launch from a submarine. The Shtil-1 launch vehicle was a converted Makeyev R-29RM SLBM. The satellite payload was placed in the standard re-entry vehicle. The launch platform was the K-407 Novomoskovsk, a 667BDRM Delfin class submarine of the Russian Northern Fleet 3rd Flotilla. The launch was made from a firing range in the Barents Sea off the coast of the Kolskiy Peninsula, at 35.3 deg E 69.3 deg N. The payloads were the Tubsat-N and Tubsat-N1 `nanosatellites'. Tubsat-N entered a 400 x 776 km x 78.9 deg orbit. Both carried small store-forward communications payloads used to keep track of transmitters placed on vehicles, migrating animals, and marine buoys. They are owned, operated and built by the Technische Universitat Berlin (TUB). Tubsat-N was the larger of the pair, with dimensions of 32x32x10.4 cm and a mass of 8.5 kg.

1998 August 21 - Barents Sea Launch Area -. Operational test Agency: VMF RF. Apogee: 1,000 km (600 mi).

1999 April 1 - Barents Sea Launch Area -. Operational test Agency: VMF RF. Apogee: 1,000 km (600 mi).

1999 October 1 - Barents Sea Launch Area -. FAILURE: Failure. Operational test Agency: VMF RF. Apogee: 10 km (6 mi).

1999 October 1 - Okhotsk -. Operational test Agency: VMF RF. Apogee: 1,000 km (600 mi).

1999 October 2 - Okhotsk -. Operational test Agency: VMF RF. Apogee: 1,000 km (600 mi).

2000 March 27 - 06:00 GMT - Barents Sea Launch Area -. Agency: VMF RF. Apogee: 1,000 km (600 mi). Three launches in one day from two submarines.

2000 March 27 - 09:00 GMT - Barents Sea Launch Area -. Operational test Agency: VMF RF. Apogee: 1,000 km (600 mi).

2000 April 6 - Barents Sea Launch Area -. Operational test Agency: VMF RF. Apogee: 1,000 km (600 mi).

2000 September 12 - Barents Sea Launch Area -. Shtil VMF RF Operational test Agency: VMF RF. Apogee: 1,000 km (600 mi).

2000 December 27 - Barents Sea Launch Area -. Operational test Agency: VMF RF. Apogee: 1,000 km (600 mi).

2001 February 16 - 10:28 GMT - Barents Sea Launch Area -. Shtil VMF RF Operational test Agency: VMF RF. Apogee: 1,000 km (600 mi).

2001 June 5 - 11:32 GMT - Barents Sea Launch Area -. Shtil VMF RF Operational test Agency: VMF RF. Apogee: 1,000 km (600 mi).

2001 July 20 - 00:31 GMT - Barents Sea Launch Area -. Cosmos 1 Solar Sail Spacecraft test Agency: VMF RF. Apogee: 412 km (256 mi). Launch delayed from April 26 and July 19 failure. The Russian Navy launched a three-stage R-29R Volna from the submarine Borisoglebsk in the Barents Sea on a suborbital flight. The payload was a joint project between the Planetary Society and NPO Lavochkin's Babakin center, and consisted of a solar sail deployment test with an inflatable reentry shield. The payload failed to separate from the final stage.

2001 September 18 - Okhotsk -. Shtil VMF RF Operational test Agency: VMF RF. Apogee: 1,000 km (600 mi).

2001 September 27 - Barents Sea Launch Area -. Shtil VMF RF Operational test Agency: VMF RF. Apogee: 1,000 km (600 mi).

2001 October 18 - 09:00 GMT - Sea-launched -. Shtil VMF RF Operational test Agency: VMF RF. Apogee: 1,000 km (600 mi). Launched from a Russian submarine in the White Sea Launch Area off Arkhangelsk - Latitude: 65.5 N, Longitude:38 E.

2002 July 12 - 00:58 GMT - Barents Sea Launch Area -. IRDT-2 re-entry vehicle test flight Agency: VMF RF. Apogee: 200 km (120 mi). The Russian Navy launched the IRDT-2 spacecraft using a surplus R-29R Volna from the submarine K-44 Ryazan. The spacecraft was launched on a suborbital trajectory from the Barents Sea and landed in Kamchatka. After third stage separation the IRDT fired a boost motor to increase its speed and then inflated the first stage of its heat shield.

2002 October 12 - 09:12 GMT - Okhotsk -. Shtil VMF RF Operational test Agency: VMF RF. Apogee: 1,000 km (600 mi).

2002 October 12 - 09:55 GMT - Barents Sea Launch Area -. Shtil VMF RF Operational test Agency: VMF RF. Apogee: 1,000 km (600 mi).

2003 October 15 - 10:03 GMT - Sea-launched -. R-29RM RSM-54 test launch Agency: VMF.

2004 February 18 - 09:30 GMT - Barents Sea Launch Area -. Sineva VMF RF FAILURE: Failure. Sineva operational test Agency: VMF RF. Apogee: 10 km (6 mi). Failure - destroyed 98 seconds after launch. Launched during a nationwide military exercise.

2004 March 17 - Barents Sea Launch Area -. Sineva VMF RF Operational test Agency: VMF RF. Apogee: 1,000 km (600 mi).

2004 June 29 - 07:25 GMT - Barents Sea Launch Area -. Operational test Agency: VMF RF. Apogee: 1,000 km (600 mi).

2004 September 8 - 04:38 GMT - Barents Sea Launch Area -. Operational test Agency: VMF RF. Apogee: 1,000 km (600 mi).

2004 September 8 - 07:38 GMT - Barents Sea Launch Area -. Agency: VMF RF. Apogee: 1,000 km (600 mi). SLBM Test - second launch in one day.

2004 November 2 - 09:25 GMT - Okhotsk -. RSM-54 test Agency: VMF RF. Apogee: 1,000 km (600 mi).

2005 June 21 - 19:46 GMT - Barents Sea Launch Area -. FAILURE: Failure. Cosmos 1 Mass: 103 kg (227 lb). Spacecraft: Parus. Agency: Planetary Society. Launched from SSBN Borisoglebsk. First orbital flight attempt of converted SLBM. Payload was solar sail demonstrator. Delayed from late 2001; March 20 and October 2002; late March, August 28 and October, 2003; February, March, April 6, May 20 and 31, 2005.

2005 August 17 - 07:06 GMT - Barents Sea Launch Area -. Sineva VMF RF RSM-54 test Agency: VMF RF. Apogee: 1,000 km (600 mi).

2005 September 30 - 08:22 GMT - Okhotsk -. Volna VMF RF RSM-50 Test Agency: VMF RF. Apogee: 1,000 km (600 mi). Search for payload at reentry site was unsuccessful. Delayed from fourth quarter 2003, May and October 2004, July 5/8, September 15 and 27, 2005.

2005 October 6 - 21:30 GMT - Barents Sea Launch Area -. IRDT-2R re-entry vehicle test flight Agency: VMF RF. Apogee: 200 km (120 mi). Suborbital test of the Demonstrator inflatable reentry technology test vehicle. The reentry vehicle could not be located in the Kamchatka Peninsula impact zone and was not recovered. Test delayed from the fourth quarter of 2003, then May and October 2004, then July 5, July 8, September 15, September 27, 2005.

2005 October 7 - 21:30 GMT - Barents Sea Launch Area -. Sineva VMF RF RSM-54 Test Agency: VMF RF. Apogee: 1,000 km (600 mi).

2006 May 26 - 18:50 GMT - Barents Sea Launch Area -. Kompass-2 Mass: 80 kg (176 lb). Spacecraft: Kompas. Agency: Izmiran. Perigee: 402 km (249 mi). Apogee: 492 km (305 mi). Inclination: 78.90 deg. Period: 93.50 min. Complex Orbital Magneto-Plasma Autonomous Small Satellite. Earthquake research satellite for the Moscow-based IZMIRAN science institute. The satellite carried detectors for electrons, UHF/VHF waves, UV emission and radiation, a radio frequency analyser for electric field waves, and a Mayak ionospheric beacon. Reports indicated that the satellite did not respond to ground commands and that its mission was abandoned.

2006 June 30 - 06:25 GMT - Barents Sea Launch Area -. Sineva VMF RF R-29RM test Agency: VMF RF. Apogee: 1,000 km (600 mi).

2006 September 9 - 11:20 GMT - Arctic Ocean -. Sineva VMF RF R-29RM test Agency: VMF RF. Apogee: 1,000 km (600 mi). Submarine K-84 Ekaterinburg launched the missile while surfaced in the ice pack from a polar location toward the Chizha impact zone on the Kanin Peninsula. The three warheads were reported to have successfuly reached their targets. This was the first Russian launch from the icepack since 29 August 1995.

2006 September 10 - 14:50 GMT - Pacific Ocean -. Volna VMF RF R-29R test Agency: VMF RF. Apogee: 1,000 km (600 mi). Submarine K-433 St Georgiy Pobedonosets launched the missile from the Pacific near Simushir Island towards an impact zone on the Kanin Peninsula. The two warheads were reported to have successfully reached their targets.

2007 August 7 - Sea-launched -. Volna VMF RF 1 RV SLBM test Agency: VMF RF. Apogee: 1,000 km (600 mi).

2007 December 17 - Barents Sea Launch Area -. Sineva VMF RF Agency: VMF RF. Apogee: 1,000 km (600 mi).

2007 December 25 - Barents Sea Launch Area -. Sineva VMF RF Agency: VMF RF. 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.
Placard, TsNIIMASH Museum,
McDowell, Jonathan, Launch Log, October 1998. Web Address when accessed: http://hea-www.harvard.edu/~jcm/space/log/launch.html.

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