Encyclopedia Astronautica

Isayev N2O4/UDMH rocket engine. 0.392 kN. In Production. Isp=252s. Small attitude control thruster in Briz upper stage propulsion system S5.98M. Total summmary impulse 14,112 kg-s. Minimum impulse 4 kg-s. Specific impulse also reported as 275 sec.

Oxidizer to Fuel Ratio: 2.

Status: In Production.
Thrust: 392 N (88 lbf).
Specific impulse: 252 s.
Burn time: 3,200 s.

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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...

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

Associated Stages
  • 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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