|
gptkbp:instanceOf
|
gptkb:rocket_engine_family
|
|
gptkbp:chamberPressure
|
980 psi (Merlin 1D)
|
|
gptkbp:countryOfOrigin
|
gptkb:United_States
|
|
gptkbp:cycle
|
gas-generator
|
|
gptkbp:designer
|
gptkb:Tom_Mueller
|
|
gptkbp:diameter
|
0.99 m (Merlin 1D)
|
|
gptkbp:firstFlight
|
2006
|
|
gptkbp:fuelType
|
gptkb:RP-1
|
|
gptkbp:gimbalRange
|
±15° (Merlin 1D)
|
|
gptkbp:hasVersion
|
gptkb:Merlin_Vacuum_(MVac)
gptkb:Merlin_1D
gptkb:Merlin_1A
gptkb:Merlin_1B
gptkb:Merlin_1C
|
|
gptkbp:ignition
|
gptkb:TEA-TEB
|
|
gptkbp:length
|
3.8 m (Merlin 1D)
|
|
gptkbp:manufacturer
|
gptkb:SpaceX
|
|
gptkbp:notableFeature
|
high reliability
designed for rapid turnaround
throttleable
|
|
gptkbp:numberOfEnginesOnFalcon9FirstStage
|
9
|
|
gptkbp:numberOfEnginesOnFalcon9SecondStage
|
1
|
|
gptkbp:oxidizer
|
liquid oxygen
|
|
gptkbp:propulsion
|
gptkb:water
|
|
gptkbp:reusable
|
designed for multiple flights
|
|
gptkbp:specificImpulseVacuum
|
282 s (Merlin 1D)
311 s (Merlin 1D)
|
|
gptkbp:status
|
active
|
|
gptkbp:successor
|
gptkb:SpaceX_Raptor
|
|
gptkbp:thrustSeaLevel
|
756 kN (Merlin 1D)
|
|
gptkbp:thrustVacuum
|
845 kN (Merlin 1D)
|
|
gptkbp:usedFor
|
orbital launch
|
|
gptkbp:usedIn
|
gptkb:Falcon_1
gptkb:Falcon_9
gptkb:Falcon_Heavy
|
|
gptkbp:usedOn
|
gptkb:Falcon_1_first_stage
gptkb:Falcon_9_Block_5
gptkb:Falcon_9_second_stage_(MVac)
Falcon Heavy side boosters
|
|
gptkbp:weight
|
470 kg (Merlin 1D)
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
SpaceX Merlin
|