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gptkbp:instance_of
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gptkb:rocket
|
|
gptkbp:aircraft_operated
|
gptkb:Saturn_V
gptkb:Saturn_IB
gptkb:Saturn_I
|
|
gptkbp:designed_by
|
gptkb:Rocketdyne
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|
gptkbp:developer
|
gptkb:1955
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|
gptkbp:diameter
|
2.4 m
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|
gptkbp:engine
|
gptkb:Rocketdyne
gptkb:J-2_family
retired
staged combustion
single chamber
|
|
gptkbp:engine_type
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gptkb:rocket
|
|
gptkbp:first_flight
|
gptkb:1966
gptkb:1975
|
|
gptkbp:fuel_type
|
gas-generator cycle
liquid oxygen and RP-1
liquid combustion
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
Rocketdyne J-2
|
|
gptkbp:inspired_by
|
J-1 engine
|
|
gptkbp:length
|
4.3 m
|
|
gptkbp:mission
|
gptkb:Skylab
gptkb:Apollo_Lunar_Module
gptkb:software
|
|
gptkbp:notable_feature
|
high thrust-to-weight ratio
part of the Apollo program
used in multiple missions
first engine to use staged combustion
part of the Saturn I launch vehicle
part of the Saturn IB launch vehicle
part of the Saturn V launch vehicle
part of the Skylab program
reusable engine design
used in crewed spaceflight missions
|
|
gptkbp:number_of_rooms
|
gptkb:musical
70 psi
|
|
gptkbp:propulsion
|
150,000 lbf
263 seconds
|
|
gptkbp:replaced_by
|
gptkb:J-2_X
|
|
gptkbp:retired
|
gptkb:1973
|
|
gptkbp:social_structure
|
liquid oxygen
|
|
gptkbp:successor
|
gptkb:J-2_X
gptkb:J-2_X_engine
|
|
gptkbp:type
|
liquid-fueled rocket engine
|
|
gptkbp:used_in
|
gptkb:Saturn_V
gptkb:Saturn_IB
gptkb:Saturn_I
|
|
gptkbp:weight
|
1,200 kg
|
|
gptkbp:bfsParent
|
gptkb:Saturn_IB
|
|
gptkbp:bfsLayer
|
4
|