gptkbp:instance_of
|
gptkb:Team_Rocket
|
gptkbp:aircraft_operated
|
gptkb:Saturn_I
|
gptkbp:check_in_time
|
150 seconds
|
gptkbp:combustor_type
|
gas-generator cycle
|
gptkbp:cooling_system
|
regenerative cooling
|
gptkbp:designed_by
|
gptkb:Rocketdyne
|
gptkbp:development
|
gptkb:1955
|
gptkbp:engine
|
gptkb:space_exploration
gptkb:Apollo_missions
gptkb:Rocketdyne
gptkb:NASA
gptkb:Team_Rocket
gptkb:historical_significance
aerospace engineering
manned spaceflight
open cycle
liquid propulsion
reliability issues
|
gptkbp:engine_configuration
|
high performance
single-chamber
single-chamber engine
|
gptkbp:engine_cost
|
high development cost
|
gptkbp:engine_power
|
gptkb:1975
high thrust
|
gptkbp:engine_reusability
|
not reusable
|
gptkbp:engine_success
|
gptkb:Apollo_11_mission
|
gptkbp:engine_type
|
liquid-fueled
|
gptkbp:exhaust_system
|
bell nozzle
|
gptkbp:first_flight
|
gptkb:1967
gptkb:1975
|
gptkbp:fuel_capacity
|
12.2 feet
19.5 feet
|
gptkbp:fuel_type
|
gptkb:RP-1
|
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:mission
|
gptkb:Apollo_program
|
gptkbp:number_of_engines
|
gptkb:5
|
gptkbp:number_of_rooms
|
one
|
gptkbp:oxidation_states
|
liquid oxygen
|
gptkbp:produces
|
gptkb:15
|
gptkbp:propulsion
|
8.1
1,500,000 lbf
1.5 million pounds
|
gptkbp:specific_impulse
|
263 seconds
|
gptkbp:successor
|
gptkb:F-1_B
|
gptkbp:used_in
|
gptkb:Saturn_V
|
gptkbp:used_in_rocket
|
gptkb:Saturn_V_rocket
|
gptkbp:water_requirement
|
12,000 pounds per minute
29,000 pounds per minute
|
gptkbp:weight
|
18,500 pounds
|
gptkbp:bfsParent
|
gptkb:Saturn_V
|
gptkbp:bfsLayer
|
4
|