|
gptkbp:instance_of
|
gptkb:rocket
|
|
gptkbp:application
|
crew missions
|
|
gptkbp:check_in_time
|
500 seconds
|
|
gptkbp:collaborations
|
NASA and private contractors
|
|
gptkbp:controls
|
digital control system
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:debut_year
|
gptkb:2009
|
|
gptkbp:design
|
high performance
Rocketdyne engineers
|
|
gptkbp:developer
|
gptkb:2006
gptkb:NASA
$1 billion
|
|
gptkbp:emissions_standard
|
converging-diverging nozzle
|
|
gptkbp:engine
|
modular design
staged combustion
single-shaft engine
|
|
gptkbp:engine_type
|
staged combustion engine
J-2 S
|
|
gptkbp:environmental_impact
|
low emissions
|
|
gptkbp:first_flight
|
gptkb:2010
|
|
gptkbp:fuel_capacity
|
high
1.5 meters
4.5 meters
|
|
gptkbp:fuel_type
|
RP-1 and liquid oxygen
gas-generator cycle
|
|
gptkbp:future_plans
|
further testing and refinement
|
|
gptkbp:historical_significance
|
successor to J-2 engine
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
Rocketdyne J-2 X
|
|
gptkbp:ignition_system
|
spark igniter
|
|
gptkbp:is_tested_for
|
gptkb:NASA_Stennis_Space_Center
ongoing
successful
|
|
gptkbp:manufacturer
|
gptkb:Rocketdyne
|
|
gptkbp:number_of_rooms
|
1000 psi
|
|
gptkbp:operational_area
|
future lunar missions
|
|
gptkbp:part_of
|
gptkb:NASA's_Space_Launch_System
|
|
gptkbp:project
|
prototype testing
|
|
gptkbp:propulsion
|
240:1
290 kilonewtons
300 kilonewtons
|
|
gptkbp:related_to
|
gptkb:Orion_spacecraft
gptkb:Ares_I
gptkb:Ares_V
|
|
gptkbp:status
|
in development
|
|
gptkbp:successor
|
gptkb:J-2
|
|
gptkbp:target_audience
|
gptkb:Mars_missions
|
|
gptkbp:targets
|
deep space exploration
|
|
gptkbp:type
|
liquid-fueled engine
|
|
gptkbp:used_in
|
gptkb:software
|
|
gptkbp:weight
|
1,200 pounds
|
|
gptkbp:bfsParent
|
gptkb:Ares_I_Launch_Vehicle
|
|
gptkbp:bfsLayer
|
7
|