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gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:application
|
spacecraft propulsion
|
|
gptkbp:check_in_time
|
approximately 1,000 seconds
|
|
gptkbp:combustor_type
|
staged combustion
3,000 K
|
|
gptkbp:components
|
gptkb:Noldor
gptkb:gasoline
gptkb:electricity
gptkb:sensors
monitoring systems
actuators
data acquisition systems
piping system
safety systems
flow meters
injector
fuel pumps
thrust chamber
oxidizer tank
emergency shutdown systems
combustion chamber
turbopump
mounting structure
control valves
valve actuators
pressure regulators
ignition system components
oxidizer pumps
|
|
gptkbp:control_system
|
closed-loop control
|
|
gptkbp:design
|
gptkb:Aerojet_Rocketdyne
|
|
gptkbp:development
|
gptkb:NASA
1960s
|
|
gptkbp:engine
|
staged combustion cycle
AJ10 family
|
|
gptkbp:engine_configuration
|
single chamber
|
|
gptkbp:engine_type
|
liquid bipropellant engine
|
|
gptkbp:environmental_impact
|
low emissions
|
|
gptkbp:exhaust_system
|
bell nozzle
|
|
gptkbp:first_flight
|
gptkb:1966
|
|
gptkbp:fuel_capacity
|
3.5 ft
8.5 ft
|
|
gptkbp:fuel_economy
|
high
|
|
gptkbp:fuel_type
|
hydrazine
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
Aerojet AJ10-137
|
|
gptkbp:ignition_system
|
hypergolic ignition
|
|
gptkbp:inspired_by
|
AJ10-118
|
|
gptkbp:is_tested_for
|
conducted at NASA facilities
|
|
gptkbp:legacy
|
influenced future rocket designs
|
|
gptkbp:manufacturer
|
gptkb:Aerojet_Rocketdyne
|
|
gptkbp:mission
|
gptkb:Apollo_program
|
|
gptkbp:notable_feature
|
restart capability
|
|
gptkbp:number_of_rooms
|
1,000 psi
|
|
gptkbp:operational_status
|
retired
|
|
gptkbp:operational_use
|
Lunar landing
|
|
gptkbp:oxidation_states
|
gptkb:nitrogen_tetroxide
|
|
gptkbp:propulsion
|
gptkb:12.5
15,000 lbf
15,000 pounds-force
N2 O4 and hydrazine
|
|
gptkbp:reliability
|
high
|
|
gptkbp:retirement_year
|
gptkb:1972
|
|
gptkbp:specific_impulse
|
300 seconds
|
|
gptkbp:successor
|
AJ10-190
|
|
gptkbp:type
|
gptkb:Team_Rocket
|
|
gptkbp:used_by
|
gptkb:United_States
|
|
gptkbp:used_in
|
gptkb:Apollo_Lunar_Module
gptkb:Mars_missions
gptkb:space_mission
satellite propulsion
|
|
gptkbp:weight
|
1,200 lb
|
|
gptkbp:bfsParent
|
gptkb:Eagle_lunar_module
|
|
gptkbp:bfsLayer
|
5
|