Vinci (rocket engine)

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Country of origin France
Designer Snecma
Manufacturer Snecma
Application Upper stage liquid rocket booster
Predecessor HM-7B
Status Under Development
Liquid-fuel engine
Propellant LOX / LH2
Cycle Expander cycle
Chamber 1
Thrust (vac.) 180 kN
Chamber pressure 60.8 bar (6.08 MPa)
Isp (vac.) 465 seconds (4.56 km/s)
Dry weight

approx. 550 kg

without nozzle: 160 kg

Vinci is a European Space Agency cryogenic liquid rocket engine currently under development. It is designed to power the new upper stage of Ariane 5, ESC-B, and will be the first European re-ignitable cryogenic upper stage engine, raising the launcher's GTO performances to 12 t.


Vinci is an expander cycle rocket engine fed with liquid hydrogen and liquid oxygen. Its biggest improvement from its predecessor, the HM7B (which powers the ESC-A), is the capability of restarting up to five times. It is also the first European expander cycle engine, removing the need for a gas generator to drive the fuel and oxidizer pumps. The engine features a carbon ceramic extendable nozzle in order to have a large, 2.15 m diameter nozzle extension with minimum length: the retracted nozzle part is deployed only after the upper stage separates from the rest of the rocket; after extension, the engine's overall length increases from 2.3 m to 4.2 m.


Although the ESC-B development was put on hold in 2003, the Vinci project has not been cancelled: at a lower pace, the engine is still being developed. On 22 December 2006, Snecma announced a new ESA contract for Vinci rocket engine long-duration and re-ignition testing. In late April 2010 the German Aerospace Center DLR announced the start of a six-month test campaign for the Vinci engine at its Lampoldshausen facility.[1] The first successful test firing of this campaign took place on 27 May 2010. The first flight test of the Vinci engine is not expected until 2016 or 2017.[2]

In 2014, NASA entertained the idea of using the Vinci instead of the RL10 for an upper stage of Space Launch System. The Vinci offers the same specific impulse but with 64% greater thrust, which would allow for a reduction of one or two of the four second stage engines for the same performance for a lower cost.[3][4]

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Comparable engines[edit]

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