Encyclopedia Astronautica
Viking 5C

SEP N2O4/UDMH rocket engine. 752 kN. Isp=278s. Used on Ariane 42L, Ariane 44L, Ariane 44LP. First flight 1988.

Thrust (sl): 670.800 kN (150,802 lbf). Thrust (sl): 68,408 kgf. Engine: 776 kg (1,710 lb). Chamber Pressure: 55.00 bar. Area Ratio: 11. Thrust to Weight Ratio: 92.8361491718405. Oxidizer to Fuel Ratio: 1.7. Coefficient of Thrust vacuum: 1.74615169837655. Coefficient of Thrust sea level: 1.56511721561793.

Unfuelled mass: 776 kg (1,710 lb).
Height: 2.87 m (9.41 ft).
Diameter: 2.22 m (7.28 ft).
Thrust: 752.00 kN (169,056 lbf).
Specific impulse: 278 s.
Specific impulse sea level: 248 s.
Burn time: 142 s.
Number: 238 .

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Associated Countries
See also
Associated Launch Vehicles
  • Ariane 44LP French orbital launch vehicle. Ariane 4 with 2 liquid rocket + 2 solid rocket strap-ons. More...
  • Ariane 44L French orbital launch vehicle. Ariane 4 with 4 liquid rocket strap-ons. More...
  • Ariane 42L French orbital launch vehicle. Ariane 4 with 2 liquid rocket strap-ons. More...

Associated Propellants
  • N2O4/UDMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. 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...

  • Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993.

Associated Stages
  • Ariane 4L N2O4/UDMH propellant rocket stage. Loaded/empty mass 43,772/4,493 kg. Thrust 752.00 kN. Vacuum specific impulse 278 seconds. More...

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