|
gptkbp:instance_of
|
gptkb:rocket
|
|
gptkbp:bfsLayer
|
3
|
|
gptkbp:bfsParent
|
gptkb:Apollo_Lunar_Module
|
|
gptkbp:check_in_time
|
approximately 8 minutes
|
|
gptkbp:controls
|
manual and automatic
computer-assisted
|
|
gptkbp:cooling_system
|
liquid-cooled
regenerative cooling
|
|
gptkbp:crew
|
2 astronauts
|
|
gptkbp:designed_by
|
gptkb:NASA
|
|
gptkbp:developer
|
1962-1969
|
|
gptkbp:elevation
|
up to 100 kilometers
|
|
gptkbp:emissions_standard
|
bell nozzle
|
|
gptkbp:engine
|
low
approximately $50 million
high reliability
high efficiency
staged combustion cycle
single engine
influenced future lunar missions
provided by NASA
after ascent phase
classified as a high-performance engine
integrated into Lunar Module
optimized for lunar ascent
proven in multiple missions
start on the lunar surface
|
|
gptkbp:engine_type
|
gptkb:rocket
|
|
gptkbp:first_ascent
|
approximately 10 minutes
|
|
gptkbp:first_flight
|
gptkb:Apollo_17
gptkb:Apollo_11
multiple ground tests
|
|
gptkbp:fuel_capacity
|
8.5 feet
4.5 feet
|
|
gptkbp:fuel_type
|
hypergolic propellant
dimethylhydrazine
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
Lunar Module Ascent Engine
|
|
gptkbp:ignition_system
|
hypergolic ignition
|
|
gptkbp:investment
|
50 psi
|
|
gptkbp:is_tested_for
|
gptkb:Marshall_Space_Flight_Center
extensive pre-flight testing
|
|
gptkbp:landing_site
|
July 20, 1969
|
|
gptkbp:launch_date
|
July 16, 1969
|
|
gptkbp:launch_site
|
gptkb:Kennedy_Space_Center
|
|
gptkbp:launch_vehicle
|
gptkb:Saturn_V
|
|
gptkbp:manufacturer
|
gptkb:Grumman_Aircraft_Engineering_Corporation
|
|
gptkbp:mission
|
gptkb:planet
gptkb:Houston,_Texas
|
|
gptkbp:number_of_rooms
|
single chamber
|
|
gptkbp:operational_status
|
retired
|
|
gptkbp:propulsion
|
3,500 pounds
2.3:1
|
|
gptkbp:social_structure
|
gptkb:nitrogen_tetroxide
|
|
gptkbp:successor
|
gptkb:Orion_Service_Module_Engine
|
|
gptkbp:used_in
|
gptkb:software
|
|
gptkbp:weight
|
1,500 pounds
|