|
gptkbp:instance_of
|
gptkb:rocket
|
|
gptkbp:bfsLayer
|
3
|
|
gptkbp:bfsParent
|
gptkb:National_Air_and_Space_Museum
gptkb:Smithsonian_National_Air_and_Space_Museum
|
|
gptkbp:application
|
gptkb:software
|
|
gptkbp:check_in_time
|
150 seconds
|
|
gptkbp:controls
|
gptkb:military_officer
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:debut_year
|
gptkb:1965
|
|
gptkbp:designed_by
|
gptkb:Rocketdyne
|
|
gptkbp:developer
|
1955-1967
|
|
gptkbp:diameter
|
12.2 ft
|
|
gptkbp:emissions_standard
|
bell nozzle
|
|
gptkbp:engine
|
gptkb:advanced_technology
gptkb:5
high performance
detailed design
modular
high reliability
historic significance
vertical
open cycle
start sequence
shutdown sequence
NASA collaboration
|
|
gptkbp:engine_type
|
liquid-fueled
F-1 A, F-1 B
|
|
gptkbp:facilities
|
Rocketdyne test facility
|
|
gptkbp:first_flight
|
gptkb:1967
|
|
gptkbp:fuel_type
|
RP-1 and Liquid Oxygen
Gas-generator cycle
turbopump
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
F-1 rocket engine
|
|
gptkbp:ignition_system
|
Hypergolic
|
|
gptkbp:impact
|
gptkb:spacecraft
|
|
gptkbp:is_tested_for
|
static fire tests
|
|
gptkbp:launch_vehicle
|
gptkb:Saturn_I
|
|
gptkbp:length
|
19.5 ft
|
|
gptkbp:maintenance
|
periodic checks
|
|
gptkbp:number_of_rooms
|
single chamber
70 psi
|
|
gptkbp:operational_status
|
retired
|
|
gptkbp:produced_by
|
gptkb:15
|
|
gptkbp:propulsion
|
263 seconds
1,500,000 lbf
81.1
|
|
gptkbp:successor
|
gptkb:F-1_B
|
|
gptkbp:used_in
|
gptkb:Saturn_V
|
|
gptkbp:water_source
|
12,000 lb/min
29,000 lb/min
|
|
gptkbp:weight
|
18,500 lb
|