|
gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:application
|
gptkb:starship
|
|
gptkbp:control_system
|
computer controlled
|
|
gptkbp:cooling_system
|
regenerative cooling
regenerative cooling system
|
|
gptkbp:design_purpose
|
high performance
|
|
gptkbp:designed_by
|
gptkb:Space_X
|
|
gptkbp:development
|
ongoing
Space X engineers
|
|
gptkbp:development_cost
|
estimated in millions
|
|
gptkbp:durability
|
designed for reuse
|
|
gptkbp:engine
|
cutting-edge technology
full-flow staged combustion
in-house at Space X
scaled up for demand
|
|
gptkbp:engine_configuration
|
modular design
vertical
iterative process
publicly available
subject to change
|
|
gptkbp:engine_development_timeline
|
aggressive schedule
|
|
gptkbp:engine_power
|
high expectations
measured in thrust-to-weight ratio
constantly evaluated
|
|
gptkbp:engine_testing_frequency
|
high
|
|
gptkbp:engine_testing_results
|
publicly shared
|
|
gptkbp:engine_testing_success
|
critical for missions
|
|
gptkbp:engine_type
|
gptkb:Team_Rocket
gptkb:Raptor_2
|
|
gptkbp:environmental_impact
|
lower than kerosene engines
|
|
gptkbp:first_flight
|
gptkb:2020
|
|
gptkbp:first_static_fire_test
|
gptkb:2019
|
|
gptkbp:fuel_economy
|
high
|
|
gptkbp:fuel_type
|
cryogenic tanks
cryogenic
|
|
gptkbp:future_plans
|
gptkb:Mars_missions
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
Raptor engine
|
|
gptkbp:ignition_system
|
spark ignition
|
|
gptkbp:inspiration
|
Mars colonization
|
|
gptkbp:investment
|
300 bar
|
|
gptkbp:involved_in
|
NASA contracts
|
|
gptkbp:is_tested_for
|
gptkb:Mc_Gregor,_Texas
gptkb:Space_X_Boca_Chica
ongoing
multiple iterations
|
|
gptkbp:is_used_in
|
gptkb:New_Glenn
|
|
gptkbp:launch_cadence
|
high frequency expected
|
|
gptkbp:launch_site
|
gptkb:Boca_Chica,_Texas
|
|
gptkbp:launch_vehicle
|
gptkb:starship
|
|
gptkbp:number_of_engines
|
gptkb:33
gptkb:6
|
|
gptkbp:number_of_rooms
|
single chamber
|
|
gptkbp:operational_use
|
planned for lunar missions
|
|
gptkbp:part_of
|
gptkb:Starship_program
|
|
gptkbp:performance
|
high efficiency
|
|
gptkbp:propulsion
|
yes
high
methane and oxygen
2300 k N
up to 2300 k N
|
|
gptkbp:safety_features
|
multiple redundancies
|
|
gptkbp:staged_combustion_cycle
|
full flow
|
|
gptkbp:successor
|
gptkb:Merlin_engine
|
|
gptkbp:thrust_chamber
|
single nozzle
|
|
gptkbp:type
|
gptkb:Team_Rocket
|
|
gptkbp:used_in
|
gptkb:starship
|
|
gptkbp:uses
|
methane
liquid oxygen
|
|
gptkbp:weight
|
approximately 1,500 kg
|
|
gptkbp:bfsParent
|
gptkb:Team_Rocket
|
|
gptkbp:bfsLayer
|
3
|