Encyclopedia Astronautica
Aestus



rdaestus.jpg
Aestus
Credit: Boeing / Rocketdyne
Friedrichshafen N2O4/MMH rocket engine. 29 kN. In production. Isp=324s. Upper stage engine for Ariane 5 developed 1988 - 1995. Original version could not be restarted; version for EPS L10 stage for Ariane 5V allowed multiple restarts. First flight 1996.

The Aestus rocket engine was developed at the Ottobrunn Space Propulsion Centre during the period 1988 - 1995. The first operational flight of Aestus was on 30 October 1997 on Ariane 5 flight 502. Helium pressure fed. Electromechanical gimbaled nozzle (9.5 deg).

Engine: 111 kg (244 lb). Chamber Pressure: 11.00 bar. Area Ratio: 84. Oxidizer to Fuel Ratio: 2.05. Restarts: 5.

Status: In production.
Height: 2.20 m (7.20 ft).
Diameter: 1.32 m (4.33 ft).
Thrust: 29.00 kN (6,519 lbf).
Specific impulse: 324 s.
Burn time: 1,100 s.
Number: 22 .

More... - Chronology...


Associated Countries
Associated Spacecraft
  • Ariane 5 EPS L10 German space tug. Study 2003. Upper stage / space tug - in production. Launched by Ariane 5V. 250 kg additional propellant compared to Ariane 5G version. More...

See also
Associated Manufacturers and Agencies
Associated Propellants
  • N2O4/MMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Monomethylhydrazine (CH3NHNH2) is a storable liquid fuel that found favour in the United States for use in orbital spacecraft engines. Its advantages in comparison to UDMH are higher density and slightly higher performance. More...

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

Associated Stages
  • Ariane 5 EPS L10 N2O4/MMH propellant rocket stage. Loaded/empty mass 12,750/2,750 kg. Thrust 27.40 kN. Vacuum specific impulse 324 seconds. 250 kg additional propellant compared to Ariane 5G version. More...
  • Ariane 5-2 N2O4/MMH propellant rocket stage. Loaded/empty mass 12,500/2,700 kg. Thrust 27.40 kN. Vacuum specific impulse 324 seconds. Storable propellant, restartable upper stage for use with Ariane 5. Chamber pressure 10 bar; expansion ratio 83.0; propellant mix ratio 2.05. Empty mass without VEB payload fairing support ring and avionics is 1200 kg. More...

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