ABOUT VINCI
Vinci is a cryogenic upper stage engine developed by ArianeGroup for the Ariane 6 rocket. It uses an expander cycle burning liquid hydrogen and liquid oxygen, providing re-ignition capability for flexible mission profiles. Vinci delivers 180 kN of thrust and represents a major upgrade over the HM7B it replaces on European upper stages.
Image: ESA
PERFORMANCE
| Thrust (Sea Level) | N/A (upper stage) kN |
| Thrust (Vacuum) | 180 kN (40,500 lbf) kN |
| ISP (Sea Level) | N/A s |
| ISP (Vacuum) | 457 s s |
| Chamber Pressure | 6.08 MPa (882 psi) bar |
| Mass | 550 kg |
| Thrust-to-Weight | 33 |
| Throttle Range | Not throttleable |
| Restart Capable | Yes (up to 5 restarts) |
THRUST CONVERSIONS (VACUUM)
| Kilonewtons | 180.0 kN |
| Pounds-force | 40,466 lbf |
ENGINE CYCLE
Expander
The expander cycle uses heat from the combustion chamber walls to vaporize fuel, which then drives the turbopumps. No propellant is wasted, making it very efficient for upper stages. Used by the RL10.
PROPULSION
| Propellant | Liquid Hydrogen (LH₂) |
| Oxidizer | LOX |
| Engine Cycle | Expander |
| Mixture Ratio | 5.8:1 |
| Flow Rate | ~40 kg/s kg/s |
PHYSICAL
| Dimensions | 2.15 m nozzle diameter × 4.2 m length |
| Combustion Chambers | 1 |
| Nozzle Expansion Ratio | 240:1:1 |
GENERAL
| Manufacturer | ArianeGroup |
| Country | France / Europe |
| Status | Active |
| First Flight | April 16, 2026 |
VARIANTS (1)
- Vinci
ENGINE LINEAGE
⚖ PROPELLANTS
🏢 MANUFACTURER
