Encyclopedia Astronautica
RDMT-12


NII Mash N2O4/UDMH rocket engine. 12 N. Almaz, Kvant, Kristall, Spektr, Priroda. In Production. Low-thrust attitude control thruster. Predecessor was RDMT-400. Used in Isayev 17D58E engine. Isp=279s.

Application: Almaz, Kvant, Kristall, Spektr, Priroda.

Engine: 0.55 kg (1.21 lb). Chamber Pressure: 9.00 bar. Thrust to Weight Ratio: 2.18.

AKA: 17D58E.
Status: In Production.
Unfuelled mass: 0.55 kg (1.21 lb).
Thrust: 12 N (2 lbf).
Specific impulse: 279 s.

More... - Chronology...


Associated Countries
See also
Associated Manufacturers and Agencies
  • NII Mash Russian manufacturer of rocket engines. NII Mash, Russia. More...

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...

Bibliography
  • Haeseler, Dietrich, Datasheets from NII Mashinostroeniye, Nishnaya Salda, 1992 via Dietrich Haeseler.

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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