Encyclopedia Astronautica

Aerojet Nitric acid/UDMH rocket engine. 41.4 kN. Isp=306s. Used on Delta upper stage for Delta 0100, Delta 1000, N-2 boosters. First flight 1972.

Engine: 95 kg (209 lb). Chamber Pressure: 9.00 bar. Area Ratio: 40. Propellant Formulation: RFNA/UDMH. Thrust to Weight Ratio: 44.4. Coefficient of Thrust vacuum: 4.71652202294704. Coefficient of Thrust sea level: .27.

Unfuelled mass: 95 kg (209 lb).
Diameter: 1.40 m (4.50 ft).
Thrust: 41.40 kN (9,307 lbf).
Specific impulse: 306 s.
Burn time: 335 s.
Number: 13 .

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Associated Countries
See also
Associated Launch Vehicles
  • N-2 Licensed version of Delta built in Japan using both US and Japanese components. 4 stage vehicle. More...
  • Delta 0100 American orbital launch vehicle. The military Thor-Delta vehicles were developed into the first of a series of commercial satellite launch vehicles. The Delta 0100 series featured Castor 2 solid propellant strap-ons and a Long Tank Thor core with MB-3 engine. More...
  • Delta 1000 American orbital launch vehicle. The Delta 1000 series used Castor 2 strap-ons and the Extended Long Tank core with MB-3 engine. 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 F Nitric acid/UDMH propellant rocket stage. Loaded/empty mass 5,629/784 kg. Thrust 41.36 kN. Vacuum specific impulse 280 seconds. More...

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