S5.98M

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S5.98M

Isayev N2O4/UDMH rocket engine. Used on Briz and Briz-M upper stages. 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.

AKA: 14D30;S5.98. Number: 15 . Thrust: 19.62 kN (4,411 lbf). Unfuelled mass: 95 kg (209 lb). Specific impulse: 326 s. Burn time: 3,200 s.

High performance storable liquid engine. 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.

Engine: 95 kg (209 lb). Thrust to Weight Ratio: 21.05. Oxidizer to Fuel Ratio: 2. Restarts: 8.

Family: Storable liquid. Country: Russia. Spacecraft: Angara Briz M. Launch Vehicles: Rokot, Proton/Briz K/M. Propellants: N2O4/UDMH. Stages: Angara Briz M stage, Briz-KM, Proton KM-4 Briz M, Rokot-3 Briz. Agency: Isayev bureau. Bibliography: 359, 409.

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