Aestus
Aestus
Credit - Boeing / Rocketdyne
Designer: Astrium. Propellants: N2O4/MMH. Thrust(vac): 29.000 kN (6,519 lbf). Isp: 324 sec. Burn time: 1,100 sec. Mass Engine: 111 kg (244 lb). Diameter: 1.32 m (4.33 ft). Length: 2.20 m (7.20 ft). Chambers: 1. Chamber Pressure: 11.00 bar. Area Ratio: 84.00. Oxidizer to Fuel Ratio: 2.05. Country: Germany. Status: In production. First Flight: 1996. Last Flight: 2005. Flown: 22.

Upper stage engine for Ariane 5. Pressure (helium) fed. Electromechanical gimbaled nozzle (9.5 deg). Original version could not be restarted; version for EPS L10 stage for Ariane 5V allowed multiple restarts. 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.

Aestus used on Rocket Stages

Aestus used on Spacecraft

Bibliography and Further Reading
  • Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993. ISBN: 5060025632. Russian-language textbook on rocket theory. More at amazon.com...
 
 
 
 
 
 
 
 
 
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