Aestus

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Aestus

Aestus
Credit: Boeing / Rocketdyne

Friedrichshafen N2O4/MMH rocket engine. In production. 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.

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.

Subtopics

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.

Family: Storable liquid. Country: Germany. Propellants: N2O4/MMH. Stages: Ariane 5-2, Ariane 5-2 EPS L10 Aestus. Agency: Friedrichshafen. Bibliography: 225.

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