S5.98M

Government Designation: 14D30. Other Designations: S5.98M. Designer: Isayev. Application: Rokot-3 Briz; Soyuz-2 Briz; Proton Briz-M. Propellants: N2O4/UDMH. Thrust(vac): 19.620 kN (4,411 lbf). Isp: 326 sec. Burn time: 3,200 sec. Mass Engine: 95 kg (209 lb). Chambers: 1. Oxidizer to Fuel Ratio: 2.00. Thrust to Weight Ratio: 21.05. Country: Russia. First Flight: 1990. Last Flight: 2006. Flown: 15.

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.

S5.98M used on Rocket Stages

Used on stage: Angara Briz M. on launch vehicle: Angara 1.1.

Used on stage: Proton KM-4 Briz M. on launch vehicle: Proton 8K82K / Briz-M.

Used on stage: Rokot-3 Briz. on launch vehicle: Rokot.

S5.98M used on Spacecraft

Used on: Angara Briz M.

Used on: Briz K.

Used on: Briz M.

Bibliography and Further Reading

Chemiy, I, Novosti kosmonavtiki, "'Rokot' - nekotrie deali", Issue 3, 1999, p. 53..

Novosti kosmonavtiki, Issue 2, 1999 via Dietrich Haeseler.

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