Isayev N2O4/UDMH rocket engine. 19.62 kN. Used on Briz and Briz-M upper stages. Isp=325s. 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.
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 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.
Application: Rokot-3 Briz; Soyuz-2 Briz; Proton Briz-M.
Engine: 95 kg (209 lb). Thrust to Weight Ratio: 21.05. Oxidizer to Fuel Ratio: 2. Restarts: 8.
AKA: S5.98M; 14D30.
More... - Chronology...
Unfuelled mass: 95 kg (209 lb).
Thrust: 19.62 kN (4,411 lbf).
Specific impulse: 326 s.
Burn time: 3,200 s.
Number: 15 .
Briz K Russian space tug. 6 launches, (1990) to (2002). Upper stage / space tug - in production. Launched by Rokot. Briz KM differed from Briz K in having 'compact' components, and a special payload truss for the Globalstar dispenser. More...
Briz M Russian space tug. 2 launches, (1999) to (2000). Upper stage / space tug - in production. New upper stage for Proton, replacing Energia Corporation's Block DM, making Proton an all-Khrunichev launch vehicle. More...
Angara Briz M Russian space tug. Study 2004. Upper stage / space tug - in development 2004. Launched by Angara launch vehicle family.. 8 restarts. Propellant ration 2.0:1. More...
Associated Launch Vehicles
Rokot Russian all-solid orbital launch vehicle, consisting of decommissioned UR-100N ICBMs with a Briz-KM upper stage. More...
Proton/Briz K/M Earlier 8K82K model Proton, but Briz M storable propellant upper stage replaced the Block D cyrogenic stage. More...
Angara The Angara was a new all-Russian heavy launch vehicle designed to replace the Zenit (which was built by a Ukrainian company) and Proton (which had launch pads only on Kazakh territory). The booster was sized for rail transport of modular manufactured components to cosmodromes at Plesetsk and Svobodniy. The design featured a single modular core that could be clustered for large payloads or used as a first stage with a variety of existing upper stages. All plans for the Angara were dependent on financing and subject to constant change. More...
Associated Manufacturers and Agencies
N2O4/UDMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Unsymmetrical Dimethylhydrazine ((CH3)2NNH2) became the storable liquid fuel of choice by the mid-1950's. Development of UDMH in the Soviet Union began in 1949. It is used in virtually all storable liquid rocket engines except for some orbital manoeuvring engines in the United States, where MMH has been preferred due to a slightly higher density and performance. More...
Novosti kosmonavtiki, Issue 2, 1999 via Dietrich Haeseler.
Chemiy, I, "'Rokot' - nekotrie deali", Novosti kosmonavtiki, Issue 3, 1999, p. 53..
Angara Briz M N2O4/UDMH propellant rocket stage. Loaded/empty mass 6,565/1,600 kg. Thrust 19.60 kN. Vacuum specific impulse 325.5 seconds. Version proposed as Angara upper stage. 8 restarts. Propellant ration 2.0:1. More...
Briz-KM N2O4/UDMH propellant rocket stage. Loaded/empty mass 6,700/1,700 kg. Thrust 19.60 kN. 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...
Proton KM-4 Briz M N2O4/UDMH propellant rocket stage. Loaded/empty mass 22,170/2,370 kg. Thrust 19.60 kN. Vacuum specific impulse 326 seconds. New upper stage for Proton, replacing Energia Corporation's Block DM, making Proton an all-Khrunichev launch vehicle. The Khrunichev-built Briz-M upper stage is a derivative of the flight-proven Briz -K stage (as used on the Rokot booster). More...
Rokot-3 Briz N2O4/UDMH propellant rocket stage. Loaded/empty mass 6,565/1,600 kg. Thrust 19.60 kN. Vacuum specific impulse 326 seconds. High performance storable liquid engine. The basic stage can be adapted with 'wrap-around' propellant tanks for Proton booster applications. More...
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