Encyclopedia Astronautica
Von Braun-1


Notional Nitric acid/UDMH rocket engine. 3057.3 kN. Study 1952. Isp=286s. Used on Von Braun launch vehicle.

Thrust (sl): 2,458.700 kN (552,738 lbf). Thrust (sl): 250,719 kgf. Propellant Formulation: WFNA/UDMH.

Status: Study 1952.
Thrust: 3,057.30 kN (687,308 lbf).
Specific impulse: 286 s.
Specific impulse sea level: 230 s.
Burn time: 84 s.

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Associated Countries
See also
Associated Launch Vehicles
  • Von Braun 1952 German winged orbital launch vehicle. Von Braun's 1952 design for a reusable space launcher used the same mass and performance calculations done in 1948. However the large parachute cannisters were replaced by deployable drag skirts. This allowed the design to be substantially less squat and more elegant than the 1948 version -- but still fatter than the sleek paintings that appeared in print! More...

Associated Propellants
  • 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...

Associated Stages
  • Von Braun 1952-1 Nitric acid/Hydrazine propellant rocket stage. Loaded/empty mass 5,500,000/700,000 kg. Thrust 141,286.30 kN. Vacuum specific impulse 257 seconds. More...

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