|
gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:application
|
launch vehicles
|
|
gptkbp:check_in_time
|
150 seconds
|
|
gptkbp:combustor_type
|
gas-generator cycle
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:debut
|
gptkb:1960
|
|
gptkbp:design_features
|
modular design
|
|
gptkbp:designed_by
|
gptkb:Rocketdyne
|
|
gptkbp:development
|
1950s
|
|
gptkbp:development_cost
|
$10 million
|
|
gptkbp:engine
|
open cycle
|
|
gptkbp:engine_configuration
|
vertical
|
|
gptkbp:engine_type
|
liquid bipropellant engine
|
|
gptkbp:environmental_impact
|
low emissions
|
|
gptkbp:exhaust_system
|
bell nozzle
|
|
gptkbp:first_flight
|
gptkb:1961
gptkb:1975
|
|
gptkbp:fuel_capacity
|
5 ft
12 ft
|
|
gptkbp:fuel_type
|
tanks
RP-1 and liquid oxygen
|
|
gptkbp:has_documentation
|
NASA archives
|
|
gptkbp:historical_significance
|
first stage of Saturn I
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
H-1 engine
|
|
gptkbp:ignition_system
|
hypergolic
|
|
gptkbp:influenced_by
|
gptkb:F-1_engine
|
|
gptkbp:is_tested_for
|
static fire tests
|
|
gptkbp:launches_supported
|
Saturn I launches
|
|
gptkbp:legacy
|
early space exploration
|
|
gptkbp:manufacturer
|
gptkb:North_American_Aviation
|
|
gptkbp:number_of_engines
|
8
|
|
gptkbp:number_of_rooms
|
60 psi
|
|
gptkbp:operational_status
|
retired
|
|
gptkbp:operational_use
|
1961-1975
|
|
gptkbp:oxidizer_storage
|
tanks
|
|
gptkbp:produces
|
gptkb:40
|
|
gptkbp:propulsion
|
150,000 lbf
|
|
gptkbp:related_to
|
liquid rocket engines
|
|
gptkbp:retirement
|
program completion
|
|
gptkbp:safety_record
|
high reliability
|
|
gptkbp:specific_impulse
|
263 seconds
|
|
gptkbp:successor
|
gptkb:J-2_engine
|
|
gptkbp:system
|
gptkb:Apollo_program
|
|
gptkbp:used_in
|
gptkb:Saturn_I
|
|
gptkbp:water_requirement
|
1,200 lb/min
2,400 lb/min
|
|
gptkbp:weight
|
1,500 lb
|
|
gptkbp:bfsParent
|
gptkb:Saturn_I
|
|
gptkbp:bfsLayer
|
5
|