|
gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:application
|
gptkb:Space_Launch_System
|
|
gptkbp:average_temperature
|
-250 to 1500 ° C
|
|
gptkbp:check_in_time
|
150 seconds
|
|
gptkbp:combustor_type
|
staged combustion
|
|
gptkbp:control_system
|
electronic control
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:debut
|
gptkb:1975
|
|
gptkbp:design_features
|
modular design
|
|
gptkbp:designed_by
|
gptkb:Moscow_Institute_of_Thermal_Technology
|
|
gptkbp:development
|
10 years
1960s
|
|
gptkbp:emissions_standard
|
low
|
|
gptkbp:engine
|
gptkb:RD-0210
staged combustion cycle
|
|
gptkbp:engine_configuration
|
two-chamber
|
|
gptkbp:environmental_impact
|
minimal
|
|
gptkbp:exhaust_system
|
bell nozzle
|
|
gptkbp:first_flight
|
gptkb:1980
|
|
gptkbp:fuel_economy
|
high
|
|
gptkbp:fuel_type
|
kerosene
|
|
gptkbp:historical_significance
|
pioneering technology
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
RD-0230 engine
|
|
gptkbp:ignition_system
|
hypergolic ignition
|
|
gptkbp:inspired_by
|
gptkb:RD-0210
|
|
gptkbp:is_tested_for
|
gptkb:Gromov_Flight_Research_Institute
gptkb:1990
extensive
|
|
gptkbp:launch_vehicle
|
gptkb:Soyuz_family
|
|
gptkbp:launches_supported
|
over 100
|
|
gptkbp:legacy
|
influenced future designs
|
|
gptkbp:manufacturer
|
gptkb:NPO_Energomash
|
|
gptkbp:notable_launches
|
gptkb:Salyut_space_stations
|
|
gptkbp:number_of_rooms
|
2
15 MPa
|
|
gptkbp:operational_use
|
gptkb:space_exploration
|
|
gptkbp:oxidation_states
|
liquid oxygen
|
|
gptkbp:produces
|
50 units
|
|
gptkbp:propulsion
|
230 k N
190:1
|
|
gptkbp:reliability
|
high
|
|
gptkbp:retirement_year
|
gptkb:1990
|
|
gptkbp:specific_impulse
|
300 seconds
|
|
gptkbp:status
|
retired
|
|
gptkbp:successor
|
gptkb:RD-0120
|
|
gptkbp:successor_engine
|
gptkb:RD-0124
|
|
gptkbp:type
|
liquid-fueled engine
|
|
gptkbp:used_in
|
gptkb:Soyuz_spacecraft
|
|
gptkbp:water_requirement
|
100 kg/s
200 kg/s
|
|
gptkbp:weight
|
1,200 kg
|
|
gptkbp:bfsParent
|
gptkb:Viktor_Mikhailovich_Glushko
|
|
gptkbp:bfsLayer
|
6
|