Nitric acid/UDMH rocket stage. 255.00 kN (57,326 lbf) thrust. Mass 15,100 kg (33,290 lb).
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Gross mass: 15,100 kg (33,200 lb).
Unfuelled mass: 2,000 kg (4,400 lb).
Height: 16.00 m (52.00 ft).
Diameter: 1.30 m (4.20 ft).
Thrust: 255.00 kN (57,326 lbf).
Burn time: 110 s.
Number: 11 .
Nodong North Korean Nitric acid/UDMH rocket engine. 144 kN. In production. Isp=255s. Used in North Korean missiles and Taepodong 1 satellite launcher. Derived from Isayev designs developed for Scud missiles and SLBM's of the Makeyev bureau. First flight 1998. More...
Associated Launch Vehicles
Shahab 3 Iranian intermediate range ballistic missile, evolved incrementally with Russian assistance from initial copy of North Korean Nodong 1 into a longer-range missile and the first stage of an orbital launch vehicle. Initial version began flight tests in 1998. 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...
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