Difference between revisions of "Merlin"
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Revision as of 03:33, 11 May 2021
| Merlin | |
|---|---|
| |
| Overview | |
| Vacuum thrust | 409 kN |
| Sealevel thrust | 342 kN |
| specific impulse (vac) | 3.0 kN·s/kg |
| Fuel | RP-1 |
| Oxidizer | LOX |
| Cycle | gas-generator cycle |
| First flight | 2006 |
| Entered service | Not in service |
| Manufacturer | SpaceX |
| Dimensions | |
| Length | Unknown |
| Width | Unknown |
| Dry mass | approx. 400 kg |
| Power head | |
| Chamber pressure | 6.14 MPa |
| Chamber temperature | Unknown |
| Fuel flow rate | Unknown |
| Oxidizer flow rate | Unknown |
The Merlin engine is a RP-1/liquid oxygen gas-generator cycle rocket engine. The Merlin engine was developed for use on the Falcon 1, Falcon 5 and Falcon 9 rockets by SpaceX and is designed for sea recovery and reuse.
Engine details
The nozzle is an inexpensive, expendable ablatively cooled carbon fiber composite.
Engine revision 1B has been enhanced over the 1A with a turbine upgrade (from 1490 kW to 1860 kW)
Performance
Current published ratings:
| General engine data | |
|---|---|
| Manufacturer | SpaceX |
| engine cycle | gas-generator cycle |
| Performance | |
| Sea level thrust | 342 kN (77,000 lbf) |
| Vacuum thrust | 409 kN (92,000 lbf) |
| Sea level Isp | 2.6 kN·s/kg (255 s) |
| Vacuum Isp | 3.0 kN·s/kg (304 s) |
| Chamber pressure | 6.14 MPa (890 psi) |
| Propellants | |
| Fuel | RP-1 rocket grade kerosene |
| Oxidizer | Liquid oxygen |
| Other information | |
| Engine mass | approx. 435 kg |
| Thrust-to-weight ratio (fully accounted) | 96 |