Glushko N2O4/UDMH rocket engine. 1745 kN. Proton stage 1. In Production. Uprated version of RD-253, developed in the 1980's. Isp=317s. First flight 1986.
Application: Proton stage 1.
Engine: 1,280 kg (2,820 lb). Chamber Pressure: 157.00 bar. Area Ratio: 26. Thrust to Weight Ratio: 139.06. Oxidizer to Fuel Ratio: 2.67.
Status: In Production.
More... - Chronology...
Unfuelled mass: 1,280 kg (2,820 lb).
Height: 2.72 m (8.92 ft).
Diameter: 1.50 m (4.90 ft).
Thrust: 1,745.00 kN (392,291 lbf).
Specific impulse: 317 s.
Specific impulse sea level: 285 s.
Burn time: 130 s.
First Launch: 1980's.
Number: 438 .
Associated Manufacturers and Agencies
Glushko Russian manufacturer of rocket engines and rockets. Glushko Design Bureau, Russia. More...
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...
Suborbital flights listing (internet post),
Glushko, V P, Razvitie Raketostroeniya, Moscow 1987 via Dietrich Haeseler.
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