Rokot Credit - Khrunichev Media Gallery

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

Manufacturer: Chelomei. Launches: 11. Success Rate: 100.00%. First Launch Date: 1990-11-20. Last Launch Date: 2006-07-28. Launch data is: continuing. 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.

Basic version with Briz-KM upper stage.

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. Liftoff Thrust: 1,900.000 kN (427,100 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).

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).

• 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: 3. 1 x Stage: 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. 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.

1990 November 20 - 04:00 GMT - Launch Site: Baikonur. Launch Complex: LC131. Launch Vehicle: Rokot. LV Configuration: Rokot No. 1L.

• Naryad-V Nation: USSR. Agency: VKS. Apogee: 1,000 km (600 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'. References: 5, 1264.

• Grand Prix Test mission Nation: USSR. Agency: VKS. Apogee: 1,000 km (600 mi). References: 5, 1836.

• Radio-ROSTO RS-15 Nation: Russia. Payload: RS-15. Mass: 70 kg (154 lb). Class: Communications. Type: Amateur Radio. 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. COSPAR: 1994-085A. USAF Sat Cat: 23439. References: 2, 5, 6.

• Simsat-1 Nation: Russia. Mass: 657 kg (1,448 lb). Class: Technology. Agency: Eurockot. Manufacturer: Krunichev. Perigee: 543 km (337 mi). Apogee: 562 km (350 mi). Inclination: 86.37 deg. Period: 95.62 min. COSPAR: 2000-026A. USAF Sat Cat: 26365. 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.References: 4, 552, 554.

• Simsat-2 Nation: Russia. Mass: 657 kg (1,448 lb). Class: Technology. Agency: Eurockot. Manufacturer: Krunichev. Perigee: 545 km (339 mi). Apogee: 557 km (346 mi). Inclination: 86.37 deg. Period: 95.59 min. COSPAR: 2000-026B. USAF Sat Cat: 26366. References: 4, 552, 554.

• GRACE 1 Nation: Germany. Payload: ESSP-2A, 'Tom'. Mass: 432 kg (952 lb). Class: Earth. Spacecraft: GRACE. Agency: DLR (Germany), NASA (U.S.). Manufacturer: Astrium. Perigee: 483 km (300 mi). Apogee: 506 km (314 mi). Inclination: 89.00 deg. COSPAR: 2002-012A. USAF Sat Cat: 27391. 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.References: 4, 552, 554.

• GRACE 2 Nation: Germany. Mass: 432 kg (952 lb). Class: Earth. Spacecraft: GRACE. Agency: DLR (Germany), NASA (U.S.). Manufacturer: Astrium. Perigee: 483 km (300 mi). Apogee: 506 km (314 mi). Inclination: 89.00 deg. COSPAR: 2002-012B. USAF Sat Cat: 27392. Gravimetry, Climatology first commercial flight delayed from November23-30, 2001, February27, March15 and 16. References: 4, 552, 554.

• Iridium SV97 Nation: USA. Program: Iridium. Mass: 690 kg (1,520 lb). Class: Communications. Spacecraft: LM 700. Agency: Iridium. Manufacturer: LM-S/Motorola. Perigee: 659 km (409 mi). Apogee: 669 km (415 mi). Inclination: 86.60 deg. Period: 98.00 min. COSPAR: 2002-031A. USAF Sat Cat: 27450. 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. References: 4, 552, 554.

• Iridium SV98 Nation: USA. Program: Iridium. Mass: 690 kg (1,520 lb). Class: Communications. Spacecraft: LM 700. Agency: Iridium. Manufacturer: LM-S/Motorola. Perigee: 658 km (408 mi). Apogee: 666 km (413 mi). Inclination: 86.60 deg. Period: 98.00 min. COSPAR: 2002-031B. USAF Sat Cat: 27451. References: 4, 552, 554.

• Monitor-E/SL Nation: Russia. Payload: Monitor E Mock-up. 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. COSPAR: 2003-031A. USAF Sat Cat: 27840. Delayed from October 2002, April 2003. Monitor-E mass model not released.

• Mimosa Nation: Czech Republic. Mass: 51 kg (112 lb). Class: Atmosphere Density. Spacecraft: Mimosa. Agency: Czech Academy of Sciences. Perigee: 316 km (196 mi). Apogee: 829 km (515 mi). Inclination: 96.80 deg. Period: 96.10 min. COSPAR: 2003-031B. USAF Sat Cat: 27841. 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.

• DTUSAT Nation: Denmark. Mass: 1.00 kg (2.20 lb). Class: Technology. Spacecraft: Cubesat. Agency: Danish Technical University. Perigee: 816 km (507 mi). Apogee: 831 km (516 mi). Inclination: 98.70 deg. Period: 101.40 min. COSPAR: 2003-031C. USAF Sat Cat: 27842. 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 Nation: Canada. Mass: 66 kg (145 lb). Class: Astrosismology. Spacecraft: Most. Agency: Canadian Space Agency. Perigee: 818 km (508 mi). Apogee: 834 km (518 mi). Inclination: 98.70 deg. Period: 101.40 min. COSPAR: 2003-031D. USAF Sat Cat: 27843. 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.

• Cute-1 Nation: Japan. Mass: 1.00 kg (2.20 lb). Class: Technology. Spacecraft: Cubesat. Agency: Tokyo Institute of Technology. Perigee: 817 km (507 mi). Apogee: 833 km (517 mi). Inclination: 98.70 deg. Period: 101.40 min. COSPAR: 2003-031E. USAF Sat Cat: 27844. CUTE-I carried engineering test equipment and was built by the Tokyo Institute of Technology.

• Quakesat Nation: USA. Mass: 3.00 kg (6.60 lb). Class: Technology. Spacecraft: Cubesat. Agency: QuakeFinder Institute. Perigee: 820 km (500 mi). Apogee: 834 km (518 mi). Inclination: 98.70 deg. Period: 101.40 min. COSPAR: 2003-031F. USAF Sat Cat: 27845. The Stanford University/Quakesat LLC Quakesat was to be used for detection of ELF radio emissions from seismic activity.

• AAU Cubesat Nation: Denmark. Mass: 1.00 kg (2.20 lb). Class: Technology. Spacecraft: Cubesat. Agency: Aalborg University. Perigee: 816 km (507 mi). Apogee: 831 km (516 mi). Inclination: 98.70 deg. Period: 101.40 min. COSPAR: 2003-031G. USAF Sat Cat: 27846. Aalborg University successfully contacted its AAU-Cubesat nanosatellite after it was separated. It carried a 100-meter-resolution Earth imaging camera.

• CanX-1 Nation: Canada. Mass: 1.00 kg (2.20 lb). Class: Technology. Spacecraft: Cubesat. Agency: University of Toronto. Perigee: 817 km (507 mi). Apogee: 831 km (516 mi). Inclination: 98.70 deg. Period: 101.40 min. COSPAR: 2003-031H. USAF Sat Cat: 27847. CanX-1, from the University of Toronto, carried a camera for attitude determination.

• CubeSat XI-IV Nation: Japan. Mass: 1.00 kg (2.20 lb). Class: Technology. Spacecraft: Cubesat. Agency: University of Tokyo. Perigee: 818 km (508 mi). Apogee: 833 km (517 mi). Inclination: 98.70 deg. Period: 101.40 min. COSPAR: 2003-031J. USAF Sat Cat: 27848. Cubesat XI carried technology tests for the University of Tokyo.

• Servis-1 Nation: Japan. Mass: 840 kg (1,850 lb). Class: Technology. Spacecraft: SERVIS. Agency: USEF. Perigee: 984 km (611 mi). Apogee: 1,016 km (631 mi). Inclination: 99.50 deg. Period: 105.10 min. COSPAR: 2003-050A. USAF Sat Cat: 28060. 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.

• Monitor-E Nation: Russia. Mass: 700 kg (1,540 lb). Class: Earth. Type: Resources. Spacecraft: Monitor. Agency: Roskosmos. Manufacturer: GKNPTs Khrunichev. Perigee: 522 km (324 mi). Apogee: 545 km (338 mi). Inclination: 97.50 deg. Period: 95.30 min. COSPAR: 2005-032A. USAF Sat Cat: 28822. Delayed from June 30, July 30, August 18 2005. Prototype lightweight earth monitoring satellite with 8-meter and 20-meter resolution cameras.

• CryoSat Nation: Europe. Mass: 717 kg (1,580 lb). Class: Earth. Type: Seasat. Spacecraft: CryoSat. Agency: ESA. Manufacturer: EADS Astrium. COSPAR: F20051008A. 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.

• Kompsat 2 Nation: Korea South. Payload: Arirang-2. Mass: 798 kg (1,759 lb). Class: Communications. Agency: KARI. Manufacturer: EADS Astrium. Perigee: 676 km (420 mi). Apogee: 701 km (435 mi). Inclination: 98.10 deg. Period: 98.50 min. COSPAR: 2006-031A. USAF Sat Cat: 29268. Carried a 1-meter-resolution Earth surveillance camera..

• McDowell, Jonathan, Jonathan's Space Home Page, Harvard University, 1997-present. Jonathan McDowell's complete on-line listing of all objects orbited and over 20,000 rocket launches Accessed at: http://www.planet4589.org/jsr.html.

• Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991 (succeeded by 2000 edition). ISBN: 1563473534. Superseded by the later editions. More at amazon.com...

• Isakowitz, Steven J, Hopkins, Joshua B, and Hopkins, Joseph P, International Reference to Space Launch Systems, AIAA, Washington DC, 2004. ISBN: 156347591X. The best reference on launch vehicles ever produced. More at amazon.com...