Encyclopedia Astronautica

RD-253 engine
Credit: Khrunichev
Glushko N2O4/UDMH rocket engine. 1746 kN. Proton KM-1. In production. Developed in 1990s. Isp=317s. First flight 1999.

Application: Proton KM-1.

Thrust (sl): 1,578.200 kN (354,793 lbf). Thrust (sl): 160,931 kgf. Engine: 1,300 kg (2,800 lb). Chamber Pressure: 157.00 bar. Thrust to Weight Ratio: 136.92.

AKA: 14D14.
Status: In production.
Unfuelled mass: 1,300 kg (2,800 lb).
Diameter: 1.23 m (4.05 ft).
Thrust: 1,746.00 kN (392,516 lbf).
Specific impulse: 317 s.
Specific impulse sea level: 285 s.
Burn time: 108 s.
First Launch: 1990-99.
Number: 24 .

More... - Chronology...

Associated Countries
See also
Associated Launch Vehicles
  • Proton/Briz K/M Earlier 8K82K model Proton, but Briz M storable propellant upper stage replaced the Block D cyrogenic stage. More...

Associated Manufacturers and Agencies
  • Glushko Russian manufacturer of rocket engines and rockets. Glushko Design Bureau, 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...

Associated Stages
  • Proton KM-1 N2O4/UDMH propellant rocket stage. Loaded/empty mass 450,400/31,000 kg. Thrust 10,532.00 kN. Vacuum specific impulse 317 seconds. More...

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