|
gptkbp:instance_of
|
gptkb:rocket
|
|
gptkbp:bfsLayer
|
3
|
|
gptkbp:bfsParent
|
gptkb:Saturn_V
|
|
gptkbp:aircraft_operated
|
gptkb:Saturn_I
|
|
gptkbp:check_in_time
|
150 seconds
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:designed_by
|
gptkb:Rocketdyne
|
|
gptkbp:developer
|
gptkb:1955
|
|
gptkbp:emissions_standard
|
bell nozzle
|
|
gptkbp:engine
|
gptkb:spacecraft
gptkb:historical_event
gptkb:1975
gptkb:5
gptkb:Apollo_missions
gptkb:Rocketdyne
gptkb:NASA
gptkb:rocket
gptkb:Apollo_11_mission
high performance
aerospace engineering
manned spaceflight
open cycle
high thrust
not reusable
liquid propulsion
high development cost
single-chamber
single-chamber engine
reliability issues
|
|
gptkbp:engine_type
|
liquid-fueled
|
|
gptkbp:first_flight
|
gptkb:1967
gptkb:1975
|
|
gptkbp:fuel_capacity
|
12.2 feet
19.5 feet
|
|
gptkbp:fuel_type
|
gptkb:RP-1
gas-generator cycle
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
F-1 engines
|
|
gptkbp:ignition_system
|
hypergolic
|
|
gptkbp:impact
|
moon landing missions
|
|
gptkbp:investment
|
50 psi
|
|
gptkbp:is_tested_for
|
static fire tests
|
|
gptkbp:is_used_in
|
gptkb:Saturn_V_rocket
|
|
gptkbp:mission
|
gptkb:software
|
|
gptkbp:number_of_rooms
|
one
|
|
gptkbp:produced_by
|
gptkb:15
|
|
gptkbp:propulsion
|
8.1
263 seconds
1,500,000 lbf
1.5 million pounds
|
|
gptkbp:social_structure
|
liquid oxygen
|
|
gptkbp:successor
|
gptkb:F-1_B
|
|
gptkbp:used_in
|
gptkb:Saturn_V
|
|
gptkbp:water_source
|
12,000 pounds per minute
29,000 pounds per minute
|
|
gptkbp:weight
|
18,500 pounds
|