| Country of origin | United States New Zealand |
|---|---|
| Designer | Rocket Lab |
| Manufacturer | Rocket Lab |
| Application | First- and second-stage engine [1] |
| Status | In development |
| Liquid-fuel engine | |
| Propellant | LOX / liquid methane[1] |
| Cycle | ORSC[2][3] |
| Configuration | |
| Chamber | 1 |
| Performance | |
| Thrust, vacuum | 200,000 lbf (890 kN) (Vacuum version)[2] |
| Thrust, sea-level | 165,000 lbf (730 kN) [2] |
| Throttle range | 100% - 50% |
| Specific impulse, vacuum | 329s (SL) 365s (Vac version)[2] |
| Burn time | multiple[3] |
| Used in | |
| Neutron | |
| References | |
| References | [2][3] |
Archimedes is a liquid-fuel rocket engine burning liquid oxygen and liquid methane in an oxidizer-rich staged combustion cycle.[2][3] It is designed by aerospace company Rocket Lab for its Neutron rocket.[1][2]
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