Credit: via Dietrich Haeseler
Yuzhnoye Nitric acid/UDMH rocket engine. 467.6 kN. Stage 2, no application. Developed 1960-63. Designed for second stage, no application. Two thrust levels. Thrust 467.6 kN + 11.8 kN / 7.65 kN. Isp=300s.
Application: Stage 2, no application.
Chambers: 1 + 4. Engine: 485 kg (1,069 lb). Chamber Pressure: 83.60 bar. Propellant Formulation: AK27/UDMH. Thrust to Weight Ratio: 98.31. Oxidizer to Fuel Ratio: 2.41.
Status: Developed 1960-63.
More... - Chronology...
Unfuelled mass: 485 kg (1,069 lb).
Height: 3.28 m (10.75 ft).
Diameter: 1.30 m (4.25 ft).
Thrust: 467.60 kN (105,121 lbf).
Specific impulse: 301 s.
Burn time: 134 s.
First Launch: 1960-63.
Associated Manufacturers and Agencies
Yuzhnoye Ukrainian manufacturer of rockets, spacecraft, and rocket engines. Yangel Design Bureau, Dnepropetrovsk, Ukraine. More...
Nitric acid/UDMH Drawing on the German World War II Wasserfall rocket, nitric acid (HNO3) became the early storable oxidiser of choice for missiles and upper stages of the 1950's. To overcome various problems with its use, it was necessary to combine the nitric acid with N2O4 and passivation compounds. These formulae were considered extremely secret at the time. By the late 1950's it was apparent that N2O4 by itself was a better oxidiser. Therefore nitric acid was almost entirely replaced by pure N2O4 in storable liquid fuel rocket engines developed after 1960. 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...
Shnyakin, V N, Shidkostnye Raketye Dvigateli - Opisanie i Osnovnye Tekhnicheskie Dannye, GKB Yuzhnoe "Yangel", Dnepropetrovsk 1996 via Dietrich Haeseler.
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