This page no longer updated from 31 October 2001. Latest version can be found at S5.98M

Government Designation: 14D30. Other Designations: S5.98M. Designer: Isayev. Application: Rokot-3 Briz; Soyuz-2 Briz; Proton Briz-M. Used on stages: Proton KM-4 Briz M, Rokot-3 Briz. Used on launch vehicles: Angara, Proton 8K82KM, Rokot. Used on spacecraft: Rokot-3 Briz, Proton KM-4 Briz M. Propellants: N2O4/UDMH Thrust(vac): 2,000 kgf. Thrust(vac): 19.62 kN. Isp: 326 sec. Burn time: 3,200 sec. Mass Engine: 95 kg. Chambers: 1. Oxidizer to Fuel Ratio: 2.00. Country: Russia. Status: In Production. First Flight: 1990. Last Flight: 1994. Flown: 3. References: 359 , 409 .

High performance storable liquid engine. Engine system consists of: main engine (2000 kgf, Isp=325.5 s) + 4 11D458 (40 kgf, Isp=252 s) + 12 17D58E (1.36 kgf, Isp=247 s). Main engine: Derivative of S5.92. 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.

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Last update 12 March 2001.
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