Vinci

Snecma, Ottobrunn LOx/LH2 rocket engine. Upper Stages. In development. Advanced expander cycle cryogenic propellant rocket engine with the capability of five in-space restarts. First hot-fire tests 2005. First flight 2010.

On 20 May 2005, the Vinci engine performed its first hot-fire test at Lampoldshausen's P4.1 test stand. Use of Vinci in the ESC-B upper stage in place of the HM-7B engine and the ESC-A (Etage Superieur Cryotechnique A) would increase the GTO payload performance of Ariane 5 to 12 metric tons. The Ottobrunn Space Propulsion Centre was responsible for the development of the Vinci Thrust Chamber under contract to Snecma. Ottobrunn developed Vinci's regeneratively cooled combustion chamber; coaxial propellant mixing injectors; dump cooled nozzle extension; gimbal joints; and the LOX and LH2 propellant shut-off valves. Engine length with the deployable nozzle extension retracted was 2.3 m. However completion of development of the ESC-B upper stage, and the Vinci engine, were put on indefinite hold in late 2005. First flight of the Vinci and ESC-B was postponed until sometime after 2010.

Engine: 280 kg (610 lb). Chamber Pressure: 61.00 bar. Restarts: 5.