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Rokot
Part of UR-100N Family
Rokot
Rokot
Credit: Khrunichev
Russian all-solid orbital launch vehicle, consisting of decommissioned UR-100N ICBMs with a Briz-KM upper stage.

AKA: 15A30;RS-18;SS-19 Mod.1;UR-100N. Status: Active. First Launch: 1990-11-20. Last Launch: 2016-06-04. Number: 29 . Payload: 1,800 kg (3,900 lb). Thrust: 1,850.00 kN (415,890 lbf). Gross mass: 107,000 kg (235,000 lb). Height: 29.10 m (95.40 ft). Diameter: 2.50 m (8.20 ft). Apogee: 200 km (120 mi).

Launch Price $ 10,500,000.

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. 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 main stage 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 summary 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.


More at: Rokot.

Family: all-solid, orbital launch vehicle. Country: Russia. Engines: RD-0235, 17D58E, RD-0232, S5.98M. Spacecraft: GOCE, MiniSil, Proteus, SKRL, SWARM, Yubeleiniy, Radio, Glonass, Strela-3, LM 700, Simsat, GRACE, Cubesat, Mimosa, Monitor, Most, SERVIS, CryoSat, KOMPSAT-2. Projects: Iridium. Launch Sites: Baikonur, Plesetsk, Baikonur LC131, Plesetsk LC133/1, Plesetsk LC133/3, Baikonur LC175/59, Baikonur LC175/2, Plesetsk LC133/4. Stages: Briz-KM, UR-100N Stage 1N, UR-100N Stage 2N. Agency: Chelomei bureau.
Photo Gallery

Start LauncerStart Launcer
Start launch vehicle canister, Svobodniy


BrizBriz
Credit: Khrunichev


Universal RocketsUniversal 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


RokotRokot
Rokot launch vehicle


RokotRokot
Credit: © Mark Wade



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