|
gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:burn_duration
|
approximately 8 minutes
|
|
gptkbp:combustion_chamber_pressure
|
approximately 100 psi
|
|
gptkbp:control_system
|
manual and automatic
electronic control system
throttleable
|
|
gptkbp:cooling_system
|
none required
no active cooling system
|
|
gptkbp:designed_for
|
gptkb:Lunar_Module
|
|
gptkbp:developed_by
|
gptkb:Grumman_Aircraft_Engineering_Corporation
|
|
gptkbp:elevation
|
approximately 100 kilometers
|
|
gptkbp:engine
|
gptkb:Northrop_Grumman
gptkb:Moon
1960s
NASA archives
extensive research conducted
in lunar orbit
innovative design features
significant in space exploration history
pressure-fed
manual override available
influenced future lunar missions
on the lunar surface
|
|
gptkbp:engine_configuration
|
modular design
detailed specifications available
single engine
|
|
gptkbp:engine_power
|
high reliability
high efficiency
high fuel efficiency
optimized for lunar ascent
|
|
gptkbp:engine_test
|
static fire tests
|
|
gptkbp:engine_type
|
gptkb:Team_Rocket
|
|
gptkbp:first_flight
|
gptkb:Apollo_11
|
|
gptkbp:fuel_capacity
|
60 inches
42 inches
|
|
gptkbp:fuel_type
|
hypergolic propellants
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
Lunar Module ascent engine
|
|
gptkbp:ignition_system
|
hypergolic ignition
pyrotechnic initiator
|
|
gptkbp:is_tested_for
|
NASA facilities
|
|
gptkbp:launch_mass
|
approximately 15,000 pounds
|
|
gptkbp:launch_site
|
gptkb:Moon
|
|
gptkbp:mission_type
|
gptkb:Mars_Rover
|
|
gptkbp:number_of_engines
|
one
|
|
gptkbp:operational_period
|
approximately 9 minutes
|
|
gptkbp:operational_status
|
retired
|
|
gptkbp:oxidation_states
|
gptkb:Nitrogen_Tetroxide
|
|
gptkbp:propulsion
|
gptkb:Aerozine_50
3,500 pounds
2.33
|
|
gptkbp:successor
|
gptkb:none
|
|
gptkbp:used_in
|
gptkb:Apollo_program
|
|
gptkbp:weight
|
approximately 1,500 pounds
|
|
gptkbp:bfsParent
|
gptkb:Apollo_11_artifacts
|
|
gptkbp:bfsLayer
|
5
|