Encyclopedia Astronautica
Rokot



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Rokot
Credit: Khrunichev
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Start Launcer
Start launch vehicle canister, Svobodniy
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Briz
Credit: Khrunichev
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Universal Rockets
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.
Credit: © Mark Wade
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Rokot
Rokot launch vehicle
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Rokot
Credit: © Mark Wade
Russian all-solid orbital launch vehicle, consisting of decommissioned UR-100N ICBMs with a Briz-KM upper stage.

LEO Payload: 1,800 kg (3,900 lb) to a 200 km orbit at 53.00 degrees. Payload: 1,000 kg (2,200 lb) to a 800 km SSO. Failures: 1. First Fail Date: 2005-10-08. Last Fail Date: 2005-10-08. Launch Price $: 15.000 million in 1999 dollars.

Stage Data - Rokot

  • Stage 1. 1 x 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. Status: In Production.
  • Stage 2. 1 x 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. Status: In Production. Comments: Engine has one main engine and four verniers. Verniers continue to burn for 19 seconds after mainstage shutoff.
  • Stage 3. 1 x Rokot-3 Briz. Gross Mass: 6,565 kg (14,473 lb). Empty Mass: 1,600 kg (3,500 lb). Thrust (vac): 19.600 kN (4,406 lbf). Isp: 326 sec. Burn time: 1,000 sec. Diameter: 2.50 m (8.20 ft). Span: 2.50 m (8.20 ft). Length: 1.30 m (4.20 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: S5.98M. Other designations: Briz K. Status: In Production. High performance storable liquid engine. Engine system consists of main engine plus four 11D458 plus twelve 17D58E vernier thrusters. Propellant load 3300 kg N2O4 + 1665 kg UDMH. Main engine: Capable of 8 restarts. Total deliverable impulse 2,000,000 kgf-s. Minimum impulse 2500 kg-s. Maximum burn time 1000 seconds; minimum time 1 second. Time between burns between 15 seconds and 5 hours. Vernier engines: 4 x 40 kgf. Specific impulse 275 sec. Total summmary impulse 14,112 kg-s. Minimum impulse 4 kg-s. Orientation engines: 12 x 1.3 kgf. Specific impulse 270 sec. Minimum impulse 0.068 kg-s. Briz KM differs from Briz K in having 'compact' components, special payload truss for Globalstar dispenser. The truss is 1.8 m in diameter and has a volume of 8.8 m3.

AKA: RS-18; UR-100N; SS-19 Mod.1; 15A30.
Status: Active.
Gross mass: 107,000 kg (235,000 lb).
Payload: 1,800 kg (3,900 lb).
Height: 29.10 m (95.40 ft).
Diameter: 2.50 m (8.20 ft).
Thrust: 1,850.00 kN (415,890 lbf).
Apogee: 200 km (120 mi).
First Launch: 1990.11.20.
Last Launch: 2011.02.01.
Number: 18 .

More... - Chronology...


Associated Countries
Associated Spacecraft
  • Radio Russian amateur radio communications satellite. 9 launches, 1978.10.26 (Radio Sputnik 1) to 1994.12.26 (Radio-ROSTO RS-15). More...
  • Strela-3 Russian military store-dump communications satellite. Operational, first launch 1985.01.15. Said to have initially been developed for the GRU. More...
  • LM 700 American communications satellite. 98 launches, 1997.05.05 (Iridium 8) to 2002.06.20 (Iridium SV98 ). The LM 700 had its first use in the Iridium system, a commercial communications network comprised of a minimum of 66 LEO spacecraft. More...
  • Simsat Russian technology satellite. 2 launched, 2000.05.16. 660 kg dummy satellite. More...
  • GRACE American earth geodetic satellite. 2 launched, 2002.03.17 (GRACE 1 ) and (GRACE 2 ). The GRACE mission was to accurately map variations in the Earth's gravity field over its 5-year lifetime. More...
  • Cubesat American low-cost nanosatellite bus. Used in dozens of launches, the first on 2003.06.30. More...
  • Mimosa Czech earth atmosphere satellite. One launch, 2003.06.30. Satellite by the Czech Astronomical Institute for study of the density of the upper atmosphere using the sensitive Macek accelerometer. More...
  • Monitor Russian earth land resources satellite. 2 launches, 2003.06.30 (Monitor-E/SL) and 2005.08.26 (Monitor-E). More...
  • Most Canadian visible astronomy satellite. One launch, 2003.06.30. MOST was a suitcase-sized microsatellite designed to probe stars and extrasolar planets by measuring tiny light variations undetectable from Earth. More...
  • SERVIS Japanese technology satellite. First launch 2003.10.30. More...
  • Cryosat European earth resources radar satellite. CryoSat carried a radar altimeter to acquire accurate measurements of the thickness of floating sea ice so that annual variations could be detected. More...
  • KOMPSAT-2 South Korean civilian surveillance satellite. One launch, 2006.07.28, Kompsat 2. More...

Associated Engines
  • 17D58E Isayev N2O4/UDMH rocket engine.13 N. In Production. Isp=247s. Small attitude control thruster used in Briz, Briz-M upper stage propulsion system S5.98M. More...
  • RD-0232 Kosberg N2O4/UDMH rocket engine. UR-100N / Rokot Stage 1. Engine unit (DU - dvigatelnaya ustanovka) consisting of 1 RD-0234 for tank pressurization and three RD-0233. First flight 1972. More...
  • RD-0235 Kosberg N2O4/UDMH rocket engine. 240 kN. UR-100N / RS-18 (SS-19) stage 2. Main engine based on RD-0217 with larger nozzle for altitude operation. Staged combustion cycle. Isp=320s. First flight 1972. More...
  • S5.98M Isayev N2O4/UDMH rocket engine. 19.62 kN. Used on Briz and Briz-M upper stages. Isp=325s. Engine system consists of: main engine (2000 kgf, Isp=325.5s) + 4x11D458 (40 kgf, Isp=252s) + 12x17D58E (1.36 kgf, Isp=247s). 8 restarts. First flight 1990. More...

See also
  • UR-100N 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. More...

Associated Manufacturers and Agencies
  • Chelomei Russian manufacturer of rockets, spacecraft, and rocket engines. Chelomei Design Bureau, Reutov, Russia. More...

Associated Programs
  • Iridium The Iridium system is a commercial communications network comprised of a constellation of 66 LEO spacecraft. The system uses L-Band to provide global communications services through portable handsets. More...

Associated Launch Sites
  • Baikonur Russia's largest cosmodrome, the only one used for manned launches and with facilities for the larger Proton, N1, and Energia launch vehicles. The spaceport ended up on foreign soil after the break-up of Soviet Union. The official designations NIIP-5 and GIK-5 are used in official Soviet histories. It was also universally referred to as Tyuratam by both Soviet military staff and engineers, and the US intelligence agencies. Since the dissolution of the Soviet Union the Russian Federation has insisted on continued use of the old Soviet 'public' name of Baikonur. In its Kazakh (Kazak) version this is rendered Baykonur. More...
  • Plesetsk Plesetsk was the Soviet Union's northern cosmodrome, used for polar orbit launches of mainly military satellites, and was at one time the busiest launch centre in the world. The collapse of the Soviet Union put the main launch site of Baikonur in Kazakh territory. It now seems that once the Proton rocket is retired, Baikonur will be abandoned and Plesetsk will be Russia's primary launch centre. Upgrades to existing launch facilities will allow advanced versions of the Soyuz rocket and the new Angara launch vehicle to be launched from Plesetsk. Plesetsk's major drawback was the lower net payload in geosynchronous orbit from a northern latitude launch site. However Russia is planning to remove the disadvantage by looping geosynchronous satellites around the moon, using lunar gravity to make the necessary orbital plane change. More...

Associated Stages
  • Briz-KM N2O4/UDMH propellant rocket stage. Loaded/empty mass 6,700/1,700 kg. Thrust 19.60 kN. Briz KM differs from Briz K in having 'compact' components, special payload truss for Globalstar dispenser. The truss is 1.8 m in diameter and has a volume of 8.8 m3. More...
  • UR-100N Stage 1N N2O4/UDMH propellant rocket stage. Loaded/empty mass 77,150/5,695 kg. Thrust 1,778.66 kN. Vacuum specific impulse 310 seconds. More...
  • UR-100N Stage 2N N2O4/UDMH propellant rocket stage. Loaded/empty mass 12,195/1,485 kg. Thrust 214.27 kN. Vacuum specific impulse 322 seconds. Engine has one main engine and four verniers. Verniers continue to burn for 19 seconds after mainstage shutoff. More...

Rokot Chronology


1990 November 20 - . 04:00 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC131. LV Family: UR-100N. Launch Vehicle: Rokot. LV Configuration: Rokot-K No. 1L.
  • Naryad-V - . Nation: USSR. Agency: VKS. Apogee: 900 km (550 mi). Summary: 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'..

1991 December 20 - . 21:31 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC175/2. Launch Pad: LC175/pad?. LV Family: UR-100N. Launch Vehicle: Rokot. LV Configuration: Rokot-K No. 3L.
  • Grand Prix test - . Nation: USSR. Agency: VKS. Apogee: 1,000 km (600 mi).

1994 December 26 - . 03:01 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC175/59. LV Family: UR-100N. Launch Vehicle: Rokot. LV Configuration: Rokot-K No. 4L.
  • Radio-ROSTO RS-15 - . Payload: RS-15. Mass: 70 kg (154 lb). Nation: Russia. Agency: RAKA. Class: Communications. Type: Amateur radio communications satellite. Spacecraft: Radio. USAF Sat Cat: 23439 . COSPAR: 1994-085A. Apogee: 2,151 km (1,336 mi). Perigee: 1,894 km (1,176 mi). Inclination: 64.8000 deg. Period: 127.70 min.

2000 May 16 - . 08:27 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/1. Launch Pad: LC133/pad?. LV Family: UR-100N. Launch Vehicle: Rokot.
  • Simsat-1 - . Mass: 657 kg (1,448 lb). Nation: Russia. Agency: Eurockot. Manufacturer: Chelomei. Class: Technology. Type: Navigation technology satellite. Spacecraft: Simsat. USAF Sat Cat: 26365 . COSPAR: 2000-026A. Apogee: 562 km (350 mi). Perigee: 543 km (337 mi). Inclination: 86.3707 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.
  • Simsat-2 - . Mass: 657 kg (1,448 lb). Nation: Russia. Agency: Eurockot. Manufacturer: Chelomei. Class: Technology. Type: Navigation technology satellite. Spacecraft: Simsat. USAF Sat Cat: 26366 . COSPAR: 2000-026B. Apogee: 557 km (346 mi). Perigee: 545 km (339 mi). Inclination: 86.3670 deg. Period: 95.59 min.

2002 March 17 - . 09:21 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/1. Launch Pad: LC133/pad?. LV Family: UR-100N. Launch Vehicle: Rokot.
  • GRACE 1 - . Payload: ESSP-2A, 'Tom'. Mass: 432 kg (952 lb). Nation: Germany. Agency: DLR; NASA. Manufacturer: Friedrichshafen. Class: Earth. Type: Seismology satellite. Spacecraft: GRACE. USAF Sat Cat: 27391 . COSPAR: 2002-012A. Apogee: 464 km (288 mi). Perigee: 446 km (277 mi). Inclination: 89.0000 deg. Period: 93.70 min. 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.
  • GRACE 2 - . Mass: 432 kg (952 lb). Nation: Germany. Agency: DLR; NASA. Manufacturer: Friedrichshafen. Class: Earth. Type: Seismology satellite. Spacecraft: GRACE. USAF Sat Cat: 27392 . COSPAR: 2002-012B. Apogee: 464 km (288 mi). Perigee: 445 km (276 mi). Inclination: 89.0000 deg. Period: 93.70 min. Summary: Gravimetry, Climatology first commercial flight delayed from November23-30, 2001, February27, March15 and 16. .

2002 June 20 - . 09:33 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/3. LV Family: UR-100N. Launch Vehicle: Rokot. LV Configuration: Rokot 492882034.
  • Iridium SV97 - . Mass: 690 kg (1,520 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed; Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 27450 . COSPAR: 2002-031A. Apogee: 669 km (415 mi). Perigee: 659 km (409 mi). Inclination: 86.6000 deg. Period: 98.00 min. Summary: 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..
  • Iridium SV98 - . Mass: 690 kg (1,520 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed; Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 27451 . COSPAR: 2002-031B. Apogee: 666 km (413 mi). Perigee: 658 km (408 mi). Inclination: 86.6000 deg. Period: 98.00 min.

2003 June 30 - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/3. LV Family: UR-100N. Launch Vehicle: Rokot. LV Configuration: Rokot / Briz-KM.
  • Cute-1 - . Mass: 1.00 kg (2.20 lb). Nation: Japan. Agency: TIT. Class: Technology. Type: Navigation technology satellite. Spacecraft: Cubesat. USAF Sat Cat: 27844 . COSPAR: 2003-031E. Apogee: 833 km (517 mi). Perigee: 817 km (507 mi). Inclination: 98.7000 deg. Period: 101.40 min. Summary: CUTE-I carried engineering test equipment and was built by the Tokyo Institute of Technology..
  • Quakesat - . Mass: 3.00 kg (6.60 lb). Nation: USA. Agency: QuakeFinder. Class: Technology. Type: Navigation technology satellite. Spacecraft: Cubesat. USAF Sat Cat: 27845 . COSPAR: 2003-031F. Apogee: 834 km (518 mi). Perigee: 820 km (500 mi). Inclination: 98.7000 deg. Period: 101.40 min. Summary: The Stanford University/Quakesat LLC Quakesat was to be used for detection of ELF radio emissions from seismic activity..
  • AAU Cubesat - . Mass: 1.00 kg (2.20 lb). Nation: Denmark. Agency: Aalborg. Class: Technology. Type: Navigation technology satellite. Spacecraft: Cubesat. USAF Sat Cat: 27846 . COSPAR: 2003-031G. Apogee: 831 km (516 mi). Perigee: 816 km (507 mi). Inclination: 98.7000 deg. Period: 101.40 min. Summary: Aalborg University successfully contacted its AAU-Cubesat nanosatellite after it was separated. It carried a 100-meter-resolution Earth imaging camera..
  • CanX-1 - . Mass: 1.00 kg (2.20 lb). Nation: Canada. Agency: Toronto. Class: Technology. Type: Navigation technology satellite. Spacecraft: Cubesat. USAF Sat Cat: 27847 . COSPAR: 2003-031H. Apogee: 831 km (516 mi). Perigee: 817 km (507 mi). Inclination: 98.7000 deg. Period: 101.40 min. Summary: CanX-1, from the University of Toronto, carried a camera for attitude determination..
  • CubeSat XI-IV - . Mass: 1.00 kg (2.20 lb). Nation: Japan. Agency: Tokyo. Class: Technology. Type: Navigation technology satellite. Spacecraft: Cubesat. USAF Sat Cat: 27848 . COSPAR: 2003-031J. Apogee: 833 km (517 mi). Perigee: 818 km (508 mi). Inclination: 98.7000 deg. Period: 101.40 min. Summary: Cubesat XI carried technology tests for the University of Tokyo..
  • DTUSAT - . Mass: 1.00 kg (2.20 lb). Nation: Denmark. Agency: Danish Technical University. Class: Technology. Type: Navigation technology satellite. Spacecraft: Cubesat. USAF Sat Cat: 27842 . COSPAR: 2003-031C. Apogee: 831 km (516 mi). Perigee: 816 km (507 mi). Inclination: 98.7000 deg. Period: 101.40 min. Summary: Danish cubesat DTUSat remained silent after release despite several attempts to contact it. Carried a 450-meter copper wire tether for lowering the satellite orbit..
  • Most - . Mass: 66 kg (145 lb). Nation: Canada. Agency: CSA. Class: Astronomy. Type: Astroseismology satellite. Spacecraft: Most. USAF Sat Cat: 27843 . COSPAR: 2003-031D. Apogee: 834 km (518 mi). Perigee: 818 km (508 mi). Inclination: 98.7000 deg. Period: 101.40 min. Summary: MOST (Microvariability and Oscillations of Stars) was a Canadian Space Agency project with a 0.15m telescope which would make photometric observations of stars down to mag 6 with 1 part per million accuracy in the 3500-7000 Angstrom band..
  • Mimosa - . Mass: 51 kg (112 lb). Nation: Czech Republic. Agency: KVR. Class: Earth. Type: Atmosphere satellite. Spacecraft: Mimosa. USAF Sat Cat: 27841 . COSPAR: 2003-031B. Apogee: 829 km (515 mi). Perigee: 316 km (196 mi). Inclination: 96.8000 deg. Period: 96.10 min. Summary: Mimosa was a 65 kg polyhedron built by Space Devices Ltd. of Praha, and operated by the Astronomical Insitute of the Czech Academy of Sciences (Astronomicky ustav AV CR). It carried an accelerometer to study atmospheric density..
  • Monitor-E/SL - . Payload: Monitor E Mock-up. Mass: 700 kg (1,540 lb). Nation: Russia. Agency: KVR. Spacecraft: Monitor. USAF Sat Cat: 27840 . COSPAR: 2003-031A. Apogee: 835 km (518 mi). Perigee: 694 km (431 mi). Inclination: 98.7000 deg. Period: 100.10 min. Summary: Delayed from October 2002, April 2003. Monitor-E mass model not released..

2003 October 30 - . 13:43 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/3. LV Family: UR-100N. Launch Vehicle: Rokot. LV Configuration: Rokot 4921921121.
  • Servis-1 - . Mass: 840 kg (1,850 lb). Nation: Japan. Agency: USEF. Class: Technology. Type: Navigation technology satellite. Spacecraft: SERVIS. USAF Sat Cat: 28060 . COSPAR: 2003-050A. Apogee: 1,016 km (631 mi). Perigee: 984 km (611 mi). Inclination: 99.5000 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.

2005 August 26 - . 18:34 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/3. LV Family: UR-100N. Launch Vehicle: Rokot.
  • Monitor-E - . Mass: 700 kg (1,540 lb). Nation: Russia. Agency: RAKA. Manufacturer: Chelomei. Class: Earth. Type: Earth resources satellite. Spacecraft: Monitor. USAF Sat Cat: 28822 . COSPAR: 2005-032A. Apogee: 545 km (338 mi). Perigee: 522 km (324 mi). Inclination: 97.5000 deg. Period: 95.30 min. Summary: 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 - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/3. LV Family: UR-100N. Launch Vehicle: Rokot. 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.. Failed Stage: 1.
  • CryoSat - . Mass: 717 kg (1,580 lb). Nation: Europe. Agency: ESA. Manufacturer: EADS Astrium. Class: Earth. Type: Sea satellite. Spacecraft: CryoSat. COSPAR: F20051008A. Summary: 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..

2006 July 28 - . 07:05 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/3. LV Family: UR-100N. Launch Vehicle: Rokot. LV Configuration: Rokot s/n 9.
  • Kompsat 2 - . Payload: Arirang-2. Mass: 798 kg (1,759 lb). Nation: Korea South. Agency: KARI. Manufacturer: EADS Astrium. Class: Communications. Type: Civilian communications satellite. Spacecraft: KOMPSAT-2. USAF Sat Cat: 29268 . COSPAR: 2006-031A. Apogee: 701 km (435 mi). Perigee: 676 km (420 mi). Inclination: 98.1000 deg. Period: 98.50 min. Summary: Carried a 1-meter-resolution Earth surveillance camera...

2008 May 23 - . 15:20 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/3. LV Family: UR-100N. Launch Vehicle: Rokot.
  • Yubileyniy - . Nation: Russia. Agency: KVR. Class: Communications. Type: Military communications satellite. Spacecraft: Strela-3. USAF Sat Cat: 32953 . COSPAR: 2008-025A. Apogee: 1,508 km (937 mi). Perigee: 1,480 km (910 mi). Inclination: 82.5000 deg. Period: 115.80 min. Summary: Test satellite with an amateur radio payload to commemorate (belatedly) the 50th anniversary of Sputnik..
  • Cosmos 2437 - . Nation: Russia. Agency: KVR. Class: Communications. Type: Military communications satellite. Spacecraft: Strela-3. USAF Sat Cat: 32954 . COSPAR: 2008-025B. Apogee: 1,510 km (930 mi). Perigee: 1,480 km (910 mi). Inclination: 82.5000 deg. Period: 115.90 min. Summary: Three Gonets store/dump communications satellites lofted in a single launch..
  • Cosmos 2438 - . Nation: Russia. Agency: KVR. Class: Communications. Type: Military communications satellite. Spacecraft: Strela-3. USAF Sat Cat: 32955 . COSPAR: 2008-025C. Apogee: 1,508 km (937 mi). Perigee: 1,477 km (917 mi). Inclination: 82.5000 deg. Period: 115.80 min.
  • Cosmos 2439 - . Nation: Russia. Agency: KVR. Class: Communications. Type: Military communications satellite. Spacecraft: Strela-3. USAF Sat Cat: 32956 . COSPAR: 2008-025D. Apogee: 1,509 km (937 mi). Perigee: 1,479 km (919 mi). Inclination: 82.5000 deg. Period: 115.80 min.

2009 March 17 - . 14:21 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/3. LV Family: UR-100N. Launch Vehicle: Rokot.
  • GOCE - . Mass: 1,100 kg (2,400 lb). Nation: Europe. Agency: KVR. Spacecraft: GOCE. USAF Sat Cat: 34602 . COSPAR: 2009-013A. Apogee: 276 km (171 mi). Perigee: 256 km (159 mi). Inclination: 96.6000 deg. Period: 89.80 min. Summary: Gravity-Field and steady-state Ocean Circulation Explorer. Carried a gravity gradiometer..

2009 July 6 - . 01:26 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/3. LV Family: UR-100N. Launch Vehicle: Rokot.
  • Cosmos 2451 - . Mass: 225 kg (496 lb). Nation: Russia. Agency: KVR. Spacecraft: Strela-3. USAF Sat Cat: 35498 . COSPAR: 2009-036A. Apogee: 1,507 km (936 mi). Perigee: 1,499 km (931 mi). Inclination: 82.5000 deg. Period: 116.00 min.
  • Cosmos 2452 - . Mass: 225 kg (496 lb). Nation: Russia. Agency: KVR. Spacecraft: Strela-3. USAF Sat Cat: 35499 . COSPAR: 2009-036B. Apogee: 1,506 km (935 mi). Perigee: 1,498 km (930 mi). Inclination: 82.5000 deg. Period: 116.00 min.
  • Cosmos 2453 - . Mass: 225 kg (496 lb). Nation: Russia. Agency: KVR. Spacecraft: Strela-3. USAF Sat Cat: 35500 . COSPAR: 2009-036C. Apogee: 1,505 km (935 mi). Perigee: 1,496 km (929 mi). Inclination: 82.5000 deg. Period: 116.00 min.

2009 November 2 - . 01:51 GMT - . Launch Site: Plesetsk. LV Family: UR-100N. Launch Vehicle: Rokot.
  • SMOS - . Nation: Europe. Agency: KVR. Spacecraft: Proteus. USAF Sat Cat: 36036 . COSPAR: 2009-059A. Apogee: 760 km (470 mi). Perigee: 759 km (471 mi). Inclination: 98.4000 deg. Period: 100.00 min. Summary: Soil Moisture and Ocean Salinity mission, obtaining climate-related data using a microwave aperture-synthesis interferometer..
  • PROBA-2 - . Mass: 130 kg (280 lb). Nation: Europe. Agency: KVR. Spacecraft: MiniSil. USAF Sat Cat: 36037 . COSPAR: 2009-059B. Apogee: 729 km (452 mi). Perigee: 709 km (440 mi). Inclination: 98.3000 deg. Period: 99.20 min. Summary: Project for On-Board Autonomy technology satellite..

2010 June 2 - . 01:58 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/3. LV Family: UR-100N. Launch Vehicle: Rokot.
  • Servis 2 - . Mass: 900 kg (1,980 lb). Nation: Japan. Agency: KVR. Class: Technology. Type: Technology satellite. Spacecraft: Servis. USAF Sat Cat: 36588 . COSPAR: 2010-023A. Apogee: 1,212 km (753 mi). Perigee: 1,185 km (736 mi). Inclination: 100.4000 deg. Period: 109.40 min. Summary: Space Environment Reliability Verification Integrated System to test usability of off-the-shelf commercial components in place of space-qualified hardware..

2010 September 8 - . 03:30 GMT - . Launch Site: Plesetsk. LV Family: UR-100N. Launch Vehicle: Rokot. LV Configuration: Rokot/Briz-KM.
  • Cosmos 2467 - . Payload: Kosmos-2467. Nation: Russia. Agency: KVR. Class: Communications. Type: Communications satellite. Spacecraft: Strela-3. USAF Sat Cat: 37152 . COSPAR: 2010-043A. Apogee: 1,508 km (937 mi). Perigee: 1,495 km (928 mi). Inclination: 82.5000 deg. Period: 116.00 min. Summary: Military store-dump communications satellite..
  • Strela 3 - . Payload: Gonets-M. Nation: Russia. Agency: KVR. Program: Strela. Class: Communications. Type: Communications satellite. Spacecraft: Strela-3. USAF Sat Cat: 37153 . COSPAR: 2010-043B. Apogee: 1,510 km (930 mi). Perigee: 1,497 km (930 mi). Inclination: 82.5000 deg. Period: 116.10 min. Summary: Civilian store-dump communications satellite..
  • Cosmos 2468 - . Payload: Kosmos-2468. Nation: Russia. Agency: KVR. Class: Communications. Type: Communications satellite. Spacecraft: Strela-3. USAF Sat Cat: 37154 . COSPAR: 2010-043C. Apogee: 1,509 km (937 mi). Perigee: 1,496 km (929 mi). Inclination: 82.5000 deg. Period: 116.00 min. Summary: Military store-dump communications satellite..

2011 February 1 - . 14:00 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/3. LV Family: UR-100N. Launch Vehicle: Rokot.
  • Cosmos 2470 - . Payload: Geo-IK-2 No. 11. Mass: 1,400 kg (3,000 lb). Nation: Russia. Class: Earth. Type: Geodetic satellite. Spacecraft: Glonass. USAF Sat Cat: 37362 . COSPAR: 2011-005A. Apogee: 1,030 km (640 mi). Perigee: 302 km (187 mi). Inclination: 99.5000 deg. Period: 98.10 min. Summary: Stranded in transfer orbit when the Rokot launch vehicle's Briz-KM upper stage failed to restart for its second burn..

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