Rokot - Credit: Khrunichev. 20,162 bytes. 14 x 101 pixels.

Launch vehicle based decommissioned Chelomei ICBMs. 106 tonne liftoff mass.

Launches: 4. Failures: 0. Success Rate: 100.00% pct. First Launch Date: 20 December 1990. Last Launch Date: 16 May 2000. LEO Payload: 1,800 kg. to: 200 km Orbit. at: 53.0 degrees. Payload: 1,000 kg. to a: sun synchronous, 800 km, 98.6 deg orbital trajectory. Liftoff Thrust: 190,000 kgf. Total Mass: 107,000 kg. Core Diameter: 2.5 m. Total Length: 29.1 m. Launch Price $: 15.00 million. in 1999 price dollars.

• Stage Number: 1. 1 x UR-100N Stage 1N Gross Mass: 77,150 kg. Empty Mass: 5,695 kg. Thrust (vac): 181,373 kgf. Isp: 310 sec. Burn time: 121 sec. Isp(sl): 285 sec. Diameter: 2.5 m. Span: 2.5 m. Length: 17.2 m. Propellants: N2O4/UDMH No Engines: 4. RD-0232

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  Start Launcer - Start launch vehicle cannister, Svobodniy 12,663 bytes. 241 x 130 pixels.

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• Stage Number: 2. 1 x UR-100N Stage 2N Gross Mass: 12,195 kg. Empty Mass: 1,485 kg. Thrust (vac): 21,850 kgf. Isp: 322 sec. Burn time: 183 sec. Diameter: 2.5 m. Span: 2.5 m. Length: 3.9 m. Propellants: N2O4/UDMH No Engines: 1. RD-0235

• Stage Number: 3. 1 x Rokot-3 Briz Gross Mass: 6,565 kg. Empty Mass: 1,600 kg. Thrust (vac): 2,000 kgf. Isp: 326 sec. Burn time: 1,000 sec. Diameter: 2.5 m. Span: 2.5 m. Length: 1.3 m. Propellants: N2O4/UDMH No Engines: 1. S5.98M

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  Briz Credit: Khrunichev. 9,907 bytes. 205 x 189 pixels.

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• R&D

  Suborbital.

• R&D

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  Universal Rockets - Chelomei's Universal Rocket Family. From left to right: 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 as flown. UR-500K configuration with Block D upper stage. Credit: © Mark Wade. 36,031 bytes. 630 x 351 pixels.

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  Suborbital.

• Radio-ROSTO RS-15 Spacecraft: Radio. Payload: RS-15. Mass: 70 kg.

• Simsat-2 Payload: Simsat-2.

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  Rokot - Rokot launch vehicle 20,480 bytes. 122 x 657 pixels.

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• Simsat-1 Payload: Simsat-1.

  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.

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  Rokot Credit: © Mark Wade. 1,694 bytes. 45 x 292 pixels.

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• 42 - Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991.
• 455 - Isakowitz, Steven J,, International Reference to Space Launch Systems Third Edition, AIAA, Washington DC, 2000.