Encyclopedia Astronautica
Briz M



brizm.jpg
Briz M
Credit: Khrunichev
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.

The Khrunichev-built Briz-M upper stage was a derivative of the flight-proven Briz -K stage (as used on the Rokot booster). The Briz-M consisted of a central cylinder and a jettisonable external propellant tank. Propellant carried was dependent on the specific mission requirements and was varied to maximize performance for the mission. The Briz-M was capable of operating, on-orbit, for a minimum of 24-hours and was controlled by a closed loop, triple redundant guidance system that was commandable in flight.

High performance storable liquid engine. Engine system consisted 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 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.

Gross mass: 22,170 kg (48,870 lb).
Unfuelled mass: 2,370 kg (5,220 lb).
Height: 2.61 m (8.56 ft).
Diameter: 2.50 m (8.20 ft).
Span: 4.10 m (13.40 ft).
Thrust: 19.60 kN (4,406 lbf).
Specific impulse: 326 s.
Number: 2 .

More... - Chronology...


Associated Countries
Associated Engines
  • S5.98M 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. More...

See also
Associated Propellants
  • 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...

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