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gptkbp:instanceOf
|
piston engine
|
|
gptkbp:AJ26
|
Aerojet-modified version
|
|
gptkbp:burnTime
|
about 300 seconds
|
|
gptkbp:chamberPressure
|
14.83 MPa
|
|
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
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
NK-33
|
|
gptkbp:length
|
3.7 m
|
|
gptkbp:manufacturer
|
gptkb:Kuznetsov_Design_Bureau
|
|
gptkbp:notableFeature
|
high thrust-to-weight ratio
high efficiency for its era
|
|
gptkbp:oxidizer
|
liquid oxygen
|
|
gptkbp:propulsion
|
gptkb:water
|
|
gptkbp:purpose
|
N1 lunar rocket program
|
|
gptkbp:reliability
|
high (in ground tests)
|
|
gptkbp:restartedProduction
|
2010s (limited)
|
|
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:totalProduced
|
ceased in 1974
|
|
gptkbp:usedBy
|
Aerojet Rocketdyne (as AJ26)
|
|
gptkbp:usedIn
|
gptkb:Antares_rocket
gptkb:N1_rocket
gptkb:Soyuz-2-1v
N1 Block A
N1 Block B
N1 Block Ch
N1 Block D
N1 Block E
N1 Block F
N1 Block G
N1 Block I
N1 Block K
N1 Block L
N1 Block Sh
N1 Block Shch
N1 Block V
N1 Block Y
N1 Block Ya
N1 Block Yu
N1 Block Z
N1 Block Zh
Orbital Sciences Antares
Soyuz-2-1v first stage
|
|
gptkbp:weight
|
1,240 kg
|
|
gptkbp:bfsParent
|
gptkb:Soyuz-2.1v
|
|
gptkbp:bfsLayer
|
6
|