|
gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:average_temperature
|
3,000 ° F
3,000 degrees Fahrenheit
|
|
gptkbp:check_in_time
|
8.5 minutes
approximately 8.5 minutes
|
|
gptkbp:combustor_type
|
staged combustion
|
|
gptkbp:control_system
|
digital
digital control system
computerized
|
|
gptkbp:cooling_system
|
active cooling
regenerative cooling
film cooling
liquid hydrogen cooling
|
|
gptkbp:debut
|
gptkb:1975
extensive
|
|
gptkbp:design_feature
|
high reliability
|
|
gptkbp:designed_by
|
gptkb:NASA
|
|
gptkbp:designed_for
|
gptkb:Space_Shuttle
|
|
gptkbp:developed_by
|
gptkb:Rocketdyne
|
|
gptkbp:development
|
1970s to 1980s
|
|
gptkbp:development_cost
|
$1 billion
|
|
gptkbp:durability
|
yes
designed for multiple flights
|
|
gptkbp:engine
|
gptkb:NASA_Marshall_Space_Flight_Center
gptkb:advanced_technology
gptkb:significant
gptkb:complex
international
ongoing
modular design
two
modular
controlled
closed cycle
various missions
advanced rocket technology
extensive records
influenced future rocket designs
comprehensive documentation available
numerous innovations introduced
controlled shutdown process
primarily for space launch vehicles
unique design features implemented
|
|
gptkbp:engine_configuration
|
vertical
detailed
detailed specifications available
modular engine design
|
|
gptkbp:engine_development_cost
|
significant investment
|
|
gptkbp:engine_operational_challenges
|
overcame various challenges
|
|
gptkbp:engine_operational_support
|
extensive operational support provided
|
|
gptkbp:engine_performance_improvements
|
continuous improvements made
|
|
gptkbp:engine_power
|
gptkb:2009
high reliability
high efficiency
optimized
extensively documented
|
|
gptkbp:engine_reusability
|
demonstrated
|
|
gptkbp:engine_test_facility
|
gptkb:NASA_Stennis_Space_Center
|
|
gptkbp:engine_testing_requirements
|
rigorous testing requirements established
|
|
gptkbp:environmental_impact
|
low
low emissions
|
|
gptkbp:exhaust_system
|
aerospike nozzle
|
|
gptkbp:first_flight
|
gptkb:1981
gptkb:STS-1
gptkb:STS-135
|
|
gptkbp:flight_style
|
135
|
|
gptkbp:fuel_capacity
|
7.5 ft
approximately 8,000 pounds
14.5 ft
|
|
gptkbp:fuel_economy
|
high
|
|
gptkbp:fuel_tank
|
external tank
|
|
gptkbp:fuel_type
|
liquid hydrogen
turbopump
cryogenic fuel
|
|
gptkbp:has_programs
|
gptkb:Space_Shuttle
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
SSME
|
|
gptkbp:ignition_system
|
hypergolic
|
|
gptkbp:is_tested_for
|
gptkb:NASA_Stennis_Space_Center
static fire tests
static fire test
|
|
gptkbp:is_used_in
|
gptkb:Space_Shuttle
|
|
gptkbp:launch_vehicle
|
gptkb:Space_Shuttle
|
|
gptkbp:maintenance
|
scheduled
every 10 flights
|
|
gptkbp:manufacturer
|
gptkb:Rocketdyne
|
|
gptkbp:maximum_chamber_pressure
|
3,000 psi
|
|
gptkbp:number_of_components
|
over 1,000
|
|
gptkbp:number_of_engines
|
three
|
|
gptkbp:number_of_rooms
|
single combustion chamber
3,000 psi
|
|
gptkbp:operational_history
|
used in 135 missions
|
|
gptkbp:operational_period
|
reusable
|
|
gptkbp:operational_status
|
retired
|
|
gptkbp:operational_use
|
gptkb:human_spaceflight
|
|
gptkbp:oxidation_states
|
liquid oxygen
cryogenic oxidizer
|
|
gptkbp:propulsion
|
yes
variable thrust
125:1
1,000,000 pounds
1,200,000 lbf
64.86
gimbaled engines
|
|
gptkbp:service
|
approximately 55 missions
|
|
gptkbp:specific_impulse
|
452 seconds
|
|
gptkbp:successor
|
gptkb:RS-25
|
|
gptkbp:type
|
liquid-fueled
|
|
gptkbp:used_in
|
gptkb:Space_Shuttle
|
|
gptkbp:uses
|
liquid oxygen
liquid hydrogen
|
|
gptkbp:water_requirement
|
1,000 pounds per second
|
|
gptkbp:weight
|
18,500 lb
|
|
gptkbp:bfsParent
|
gptkb:Space_Shuttle
|
|
gptkbp:bfsLayer
|
4
|