|
gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:application
|
gptkb:Space_Launch_System
|
|
gptkbp:average_temperature
|
up to 3000 K
|
|
gptkbp:check_in_time
|
150 seconds
|
|
gptkbp:combustor_type
|
staged combustion
|
|
gptkbp:control_system
|
manual and automatic
|
|
gptkbp:debut
|
gptkb:1964
|
|
gptkbp:designed_by
|
gptkb:Moscow_Institute_of_Thermal_Technology
|
|
gptkbp:development
|
1950s
|
|
gptkbp:development_cost
|
classified
|
|
gptkbp:diameter
|
1.5 m
|
|
gptkbp:engine
|
open cycle
|
|
gptkbp:engine_configuration
|
vertical
|
|
gptkbp:exhaust_system
|
bell nozzle
|
|
gptkbp:first_flight
|
gptkb:1980s
gptkb:1966
|
|
gptkbp:fuel_type
|
gptkb:RP-1
kerosene
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
RD-0210 engine
|
|
gptkbp:ignition_system
|
hypergolic
|
|
gptkbp:is_tested_for
|
gptkb:GIK-1
gptkb:Moscow
|
|
gptkbp:launched
|
over 100
|
|
gptkbp:length
|
3.5 m
|
|
gptkbp:number_of_engines
|
gptkb:4
|
|
gptkbp:number_of_rooms
|
6.5 MPa
single chamber
|
|
gptkbp:oxidation_states
|
gptkb:LOX
liquid oxygen
|
|
gptkbp:propellant_mass_flow_rate
|
250 kg/s
|
|
gptkbp:propulsion
|
100 k N
333:1
|
|
gptkbp:replaced_by
|
gptkb:RD-0120_engine
|
|
gptkbp:specific_impulse
|
300 seconds
|
|
gptkbp:status
|
retired
|
|
gptkbp:success_rate
|
95%
|
|
gptkbp:type
|
liquid propellant engine
|
|
gptkbp:used_by
|
gptkb:Soviet_space_program
|
|
gptkbp:used_in
|
gptkb:Soyuz_spacecraft
|
|
gptkbp:weight
|
300 kg
|
|
gptkbp:bfsParent
|
gptkb:Viktor_Mikhailovich_Glushko
|
|
gptkbp:bfsLayer
|
6
|