|
gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:application
|
military and commercial launches
|
|
gptkbp:combustor_type
|
gas-generator cycle
3,300 K
|
|
gptkbp:control_system
|
digital control
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:designated_as
|
Atlas and Titan rockets
|
|
gptkbp:development
|
1960s
|
|
gptkbp:engine
|
gptkb:California
gptkb:F-1
modular design
staged combustion
influenced future designs
technical manuals available
|
|
gptkbp:engine_configuration
|
single chamber
detailed specifications available
Rocketdyne engineers
|
|
gptkbp:engine_power
|
high performance
high reliability
documented performance metrics.
|
|
gptkbp:engine_thrust_vector_control
|
yes
|
|
gptkbp:engine_type
|
gas generator cycle
|
|
gptkbp:environmental_impact
|
low emissions
|
|
gptkbp:exhaust_system
|
converging-diverging nozzle
|
|
gptkbp:facilities
|
Rocketdyne test facility
|
|
gptkbp:first_flight
|
1970s
|
|
gptkbp:fuel_capacity
|
12 ft
4 ft
|
|
gptkbp:fuel_type
|
gptkb:RP-1
RP-1 and liquid oxygen
turbopump
|
|
gptkbp:has_programs
|
gptkb:NASA
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
Rocketdyne RS-37
|
|
gptkbp:ignition_system
|
hypergolic
|
|
gptkbp:is_tested_for
|
static fire tests
|
|
gptkbp:location
|
gptkb:California
|
|
gptkbp:manufacturer
|
gptkb:Rocketdyne
|
|
gptkbp:mission
|
military satellite launches
|
|
gptkbp:number_of_rooms
|
1,200 psi
|
|
gptkbp:operated_by
|
NASA and military contractors
|
|
gptkbp:operational_status
|
retired
|
|
gptkbp:oxidation_states
|
liquid oxygen
|
|
gptkbp:propulsion
|
24:1
37,000 lbf
|
|
gptkbp:retirement_year
|
1990s
|
|
gptkbp:specific_impulse
|
300 seconds
|
|
gptkbp:successor
|
gptkb:RS-68
|
|
gptkbp:successor_engine
|
gptkb:RS-68
|
|
gptkbp:type
|
gptkb:Team_Rocket
|
|
gptkbp:used_by
|
gptkb:United_States_Air_Force
|
|
gptkbp:used_in
|
satellite launch vehicles
|
|
gptkbp:weight
|
1,500 lb
|
|
gptkbp:bfsParent
|
gptkb:H-IIA_246_rocket
|
|
gptkbp:bfsLayer
|
5
|