| Country of origin | United States New Zealand |
|---|---|
| Designer | Rocket Lab |
| Manufacturer | Rocket Lab |
| Application | First- and second-stage engine |
| Status | In development |
| Liquid-fuel engine | |
| Propellant | LOX / CH4 |
| Cycle | Oxidizer-rich staged combustion |
| Configuration | |
| Chamber | 1 |
| Performance | |
| Thrust, vacuum | 890 kN (200,000 lbf) |
| Thrust, sea-level | 730 kN (165,000 lbf) |
| Throttle range | 50–100% |
| Specific impulse, vacuum | 365 s (3.58 km/s) |
| Specific impulse, sea-level | 329 s (3.23 km/s) |
| Used in | |
| Neutron | |
| References | |
| References | [1][2] |
Archimedes is a liquid-fuel rocket engine burning liquid oxygen and liquid methane in an oxidizer-rich staged combustion cycle.[1][2] It is designed by aerospace company Rocket Lab for its Neutron rocket.[3][1]
rlweb-20220921 was invoked but never defined (see the help page).rlyoutube-20220921 was invoked but never defined (see the help page).rlweb-20211202 was invoked but never defined (see the help page).