Statements (59)
Predicate | Object |
---|---|
gptkbp:instance_of |
gptkb:rocket
|
gptkbp:bfsLayer |
3
|
gptkbp:bfsParent |
gptkb:Apollo_Lunar_Module
gptkb:software |
gptkbp:check_in_time |
approximately 10 minutes
|
gptkbp:controls |
manual and automatic
throttleable |
gptkbp:cooling_system |
regenerative cooling
|
gptkbp:developed_by |
gptkb:Grumman_Aircraft_Engineering_Corporation
|
gptkbp:developer |
1962-1969
|
gptkbp:emissions_standard |
bell nozzle
|
gptkbp:engine |
gptkb:Northrop_Grumman
gptkb:NASA's_Apollo_program modular design high efficiency performance evaluations engineering manuals single engine NASA technical reports influenced future lunar missions controlled shutdown advanced propulsion technology multiple aerospace contractors aerodynamics and thermodynamics studies after Apollo program completion detailed engineering drawings two start cycles |
gptkbp:engine_type |
liquid bipropellant engine
|
gptkbp:first_flight |
gptkb:Apollo_17
gptkb:Apollo_11 |
gptkbp:fuel_capacity |
8.5 feet
1,000 gallons 4.5 feet |
gptkbp:fuel_type |
RP-1 and liquid oxygen
Inconel |
gptkbp:historical_significance |
first engine to land humans on the Moon
|
https://www.w3.org/2000/01/rdf-schema#label |
Lunar Module Descent Engine
|
gptkbp:ignition_system |
hypergolic
|
gptkbp:impact |
space exploration advancements
|
gptkbp:investment |
1,000 psi
|
gptkbp:is_designed_for |
gptkb:Apollo_Lunar_Module
|
gptkbp:is_tested_for |
gptkb:NASA_Marshall_Space_Flight_Center
gptkb:NASA_Kennedy_Space_Center static fire tests |
gptkbp:launch_vehicle |
gptkb:Saturn_V
|
gptkbp:mission |
landing on the Moon
|
gptkbp:operational_area |
two-phase operation
|
gptkbp:operational_status |
retired
|
gptkbp:propulsion |
6.67
10,000 pounds |
gptkbp:safety_features |
redundant systems
|
gptkbp:used_in |
gptkb:Apollo_14_mission
gptkb:Apollo_11_mission Apollo 12 mission Apollo 15 mission Apollo 16 mission Apollo 17 mission |
gptkbp:valve_configuration |
solenoid valves
|
gptkbp:weight |
1,500 pounds
|