|
gptkbp:instanceOf
|
gptkb:piston_engine
|
|
gptkbp:burnTime
|
about 360 seconds
|
|
gptkbp:combustionChambers
|
1
|
|
gptkbp:countryOfOrigin
|
gptkb:Soviet_Union
|
|
gptkbp:culturalHeritage
|
derived from NK-15
|
|
gptkbp:diameter
|
1.5 m
|
|
gptkbp:engineCycle
|
oxidizer-rich staged combustion
|
|
gptkbp:exportedTo
|
gptkb:United_States
|
|
gptkbp:firstFlight
|
1971
|
|
gptkbp:fuelType
|
kerosene
|
|
gptkbp:gimbalRange
|
±6 degrees
|
|
gptkbp:length
|
3.7 m
|
|
gptkbp:manufacturer
|
gptkb:Kuznetsov_Design_Bureau
|
|
gptkbp:nozzleExpansionRatio
|
36
|
|
gptkbp:numberBuilt
|
about 150
|
|
gptkbp:oxidizer
|
liquid oxygen
|
|
gptkbp:propulsion
|
gptkb:water
|
|
gptkbp:purpose
|
N1 lunar rocket
|
|
gptkbp:specificImpulseVacuum
|
297 s
331 s
|
|
gptkbp:status
|
in limited use
|
|
gptkbp:storage
|
long-term storage after N1 cancellation
|
|
gptkbp:thrustSeaLevel
|
1,510 kN
|
|
gptkbp:thrustVacuum
|
1,630 kN
|
|
gptkbp:USDesignation
|
gptkb:AJ26
|
|
gptkbp:usedIn
|
gptkb:Antares_rocket
gptkb:N1_rocket
gptkb:Soyuz-2-1v
|
|
gptkbp:weight
|
1,240 kg
|
|
gptkbp:bfsParent
|
gptkb:Kuznetsov_Design_Bureau
|
|
gptkbp:bfsLayer
|
8
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
NK-33 engine
|