Difference between revisions of "Merlin"
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| + | {{Infobox rocket engine|name=Merlin|thrust_vac=409 kN|thrust_sl=342 kN|isp_vac=3.0 kN·s/kg|cycle=[[gas-generator cycle]]|fuel=[[RP-1]]|oxidizer=[[LOX]]|first_flight_date=2006|service_date=Not in service|manufacturer=[[SpaceX]]|pc=6.14 MPa|dry_mass=approx. 400 kg}} | ||
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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. | 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 | + | ==Engine details== |
| − | The nozzle is an inexpensive, expendable [[ablatively cooled]] carbon fiber composite. | + | The nozzle is an inexpensive, expendable [[Ablative cooling|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== | |
| − | |||
| − | |||
| − | |||
| − | |||
| − | |||
| − | Engine | + | Current published ratings: |
| − | + | {| | |
| − | + | |- | |
| − | + | !bgcolor="lightblue" colspan="2"|General engine data | |
| + | |- | ||
| + | !Manufacturer | ||
| + | |[[SpaceX]] | ||
| + | |- | ||
| + | ![[engine cycle]] | ||
| + | |[[gas-generator cycle]] | ||
| + | |- | ||
| + | !bgcolor="lightblue" colspan="2"|Performance | ||
| + | |- | ||
| + | !Sea level thrust | ||
| + | |342 kN (77,000 lbf) | ||
| + | |- | ||
| + | !Vacuum thrust | ||
| + | |409 kN (92,000 lbf) | ||
| + | |- | ||
| + | !Sea level I<sub>sp</sub> | ||
| + | |2.6 kN·s/kg (255 s) | ||
| + | |- | ||
| + | !Vacuum I<sub>sp</sub> | ||
| + | |3.0 kN·s/kg (304 s) | ||
| + | |- | ||
| + | !Chamber pressure | ||
| + | |6.14 MPa (890 psi) | ||
| + | |- | ||
| + | !bgcolor="lightblue" colspan="2"|Propellants | ||
| + | |- | ||
| + | !Fuel | ||
| + | |[[RP-1]] rocket grade kerosene | ||
| + | |- | ||
| + | !Oxidizer | ||
| + | |[[Liquid oxygen]] | ||
| + | |- | ||
| + | !bgcolor="lightblue" colspan="2"|Other information | ||
| + | |- | ||
| + | !Engine mass | ||
| + | |approx. 435 kg | ||
| + | |- | ||
| + | !Thrust-to-weight ratio (fully accounted) | ||
| + | |96 | ||
| + | |- | ||
| + | |} | ||
| − | |||
| − | |||
| − | [[Category: | + | [[Category: Articles]] |
| + | [[Category:Rocket engines]] | ||
{{Stub}} | {{Stub}} | ||
Latest revision as of 03:28, 15 October 2022
| 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[edit]
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[edit]
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 |