|
gptkbp:instanceOf
|
piston engine
|
|
gptkbp:countryOfOrigin
|
gptkb:United_States
|
|
gptkbp:culturalHeritage
|
over 50 years of flight history
|
|
gptkbp:cycle
|
expander cycle
|
|
gptkbp:diameter
|
1.5 m
|
|
gptkbp:firstFlight
|
1963
|
|
gptkbp:fuelType
|
liquid hydrogen
|
|
gptkbp:gimbalRange
|
4 degrees
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
RL10 (second stage)
|
|
gptkbp:length
|
2.2 m
|
|
gptkbp:manufacturer
|
gptkb:Aerojet_Rocketdyne
|
|
gptkbp:mass
|
277 kg
|
|
gptkbp:notableFor
|
first liquid hydrogen rocket engine in operational use
|
|
gptkbp:notableMission
|
gptkb:Juno
gptkb:Mars_Science_Laboratory
gptkb:New_Horizons
gptkb:Surveyor_lunar_landers
gptkb:Voyager_missions
|
|
gptkbp:oxidizer
|
liquid oxygen
|
|
gptkbp:propulsion
|
gptkb:water
|
|
gptkbp:restartable
|
yes
|
|
gptkbp:specificImpulseVacuum
|
450 seconds
|
|
gptkbp:status
|
in production
|
|
gptkbp:thrustVacuum
|
110 kN
|
|
gptkbp:usedFor
|
planetary missions
upper stage propulsion
geostationary transfer orbit
trans-lunar injection
Earth orbit insertion
spacecraft insertion
|
|
gptkbp:usedIn
|
gptkb:Centaur_upper_stage
gptkb:Delta_Cryogenic_Second_Stage
gptkb:Saturn_IB_S-IVB_stage
gptkb:Saturn_I_S-IV_stage
|
|
gptkbp:usedOn
|
gptkb:Atlas_V
gptkb:Delta_IV
gptkb:Titan_IIIE
gptkb:Delta_III
gptkb:Saturn_I
gptkb:Saturn_IB
gptkb:Atlas-Centaur
gptkb:Titan_IV
gptkb:Vulcan_Centaur
|
|
gptkbp:variant
|
gptkb:RL10B-2
gptkb:RL10A-3
gptkb:RL10A-4
gptkb:RL10C-1
gptkb:RL10C-2
|
|
gptkbp:bfsParent
|
gptkb:Atlas_V_541
|
|
gptkbp:bfsLayer
|
6
|