Encyclopedia Astronautica
AJ10-118D


Aerojet Nitric acid/UDMH rocket engine. 33.7 kN. Isp=278s. Used on Delta B, Delta C, Delta D upper stages. First flight 1962.

Engine: 90 kg (198 lb). Chamber Pressure: 7.00 bar. Area Ratio: 40. Propellant Formulation: RFNA/UDMH. Thrust to Weight Ratio: 38.1777777777778. Coefficient of Thrust vacuum: 13.7217788312386. Coefficient of Thrust sea level: 8.00749311695287.

Unfuelled mass: 90 kg (198 lb).
Diameter: 0.84 m (2.75 ft).
Thrust: 33.70 kN (7,576 lbf).
Specific impulse: 278 s.
Burn time: 170 s.
Number: 24 .

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Associated Countries
See also
Associated Launch Vehicles
  • Delta B American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DM-21 + 1 x AJ10-118A + 1 x Altair More...
  • Delta D American orbital launch vehicle. Four stage vehicle consisting of 3 x Castor + 1 x Thor DSV-2C + 1 x Delta D + 1 x Altair 2 More...
  • Delta C American orbital launch vehicle. Unaugmented Thor with Delta D and solid propellant upper stages. More...

Associated Manufacturers and Agencies
  • Aerojet American manufacturer of rockets, spacecraft, and rocket engines. Aerojet, Sacramento, CA, USA. 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
  • Delta D Nitric acid/UDMH propellant rocket stage. Loaded/empty mass 2,693/545 kg. Thrust 33.70 kN. Vacuum specific impulse 278 seconds. More...

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