Credit: Boeing / Rocketdyne
Status: In production. Number: 22 . Thrust: 29.00 kN (6,519 lbf). Specific impulse: 324 s. Burn time: 1,100 s. Height: 2.20 m (7.20 ft). Diameter: 1.32 m (4.33 ft).
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.
|Aestus-2 Rocketdyne / DASA N2O4/MMH rocket engine. Production. Restartable upper-stage engine, began test firings at Lampoldshausen in February 2000.|
|Aestus DASA/Rocketdyne Rocketdyne rocket engine. Dasa (Germany)/Rocketdyne Non-Toxic Shuttle OMS. Gas generator, pump-fed. Name later reapplied to storable propellant engine for Ariane 5.|
|RS-72 Rocketdyne, Ottobrunn N2O4/MMH rocket engine. Aestus engine enhanced with the addition of a Boeing-Rocketdyne XLR 32 turbo-pump.|