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gptkbp:instance_of
|
gptkb:rocket
|
|
gptkbp:application
|
gptkb:software
|
|
gptkbp:average_temperature
|
3,300 ° F
|
|
gptkbp:check_in_time
|
150 seconds
|
|
gptkbp:controls
|
manual and automatic
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:debut_year
|
used in 13 launches
|
|
gptkbp:design
|
high reliability
|
|
gptkbp:designed_by
|
gptkb:Rocketdyne
|
|
gptkbp:developer
|
gptkb:1955
$18 million
|
|
gptkbp:diameter
|
12.2 ft
|
|
gptkbp:engine
|
gptkb:5
open cycle
single combustion chamber
|
|
gptkbp:engine_type
|
liquid bipropellant engine
|
|
gptkbp:first_flight
|
gptkb:1967
gptkb:1973
|
|
gptkbp:fuel_capacity
|
12,000 lb/min
0.25 lb/lbf·h
|
|
gptkbp:fuel_type
|
gptkb:RP-1_tank
gptkb:RP-1
gas-generator cycle
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
Rocketdyne F-1
|
|
gptkbp:ignition_system
|
hypergolic
|
|
gptkbp:inspired
|
gptkb:F-1_B
|
|
gptkbp:is_tested_for
|
static fire tests
Rocketdyne test facility
|
|
gptkbp:launch_vehicle
|
gptkb:Saturn_IB
|
|
gptkbp:legacy
|
influenced future rocket designs
|
|
gptkbp:length
|
19.5 ft
|
|
gptkbp:manufacturer
|
gptkb:North_American_Aviation
|
|
gptkbp:metabolism
|
29,000 lb/min
|
|
gptkbp:notable_feature
|
largest single-chamber liquid-fueled rocket engine
|
|
gptkbp:number_of_rooms
|
70 psi
|
|
gptkbp:operational_status
|
retired
|
|
gptkbp:performance
|
high thrust-to-weight ratio
|
|
gptkbp:propulsion
|
gptkb:battle
1,500,000 lbf
81:1
|
|
gptkbp:retirement_year
|
end of Apollo program
|
|
gptkbp:social_structure
|
liquid oxygen
|
|
gptkbp:storage
|
LOX tank
|
|
gptkbp:successor
|
gptkb:F-1_A
|
|
gptkbp:used_in
|
gptkb:Saturn_V
gptkb:Saturn_I
|
|
gptkbp:weight
|
18,500 lb
|
|
gptkbp:bfsParent
|
gptkb:Saturn_V
|
|
gptkbp:bfsLayer
|
3
|