|
gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:application
|
launch vehicles
|
|
gptkbp:check_in_time
|
150 seconds
|
|
gptkbp:combustor_type
|
staged combustion
|
|
gptkbp:control_system
|
gptkb:manual
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:designed_by
|
gptkb:Kuznetsov_Design_Bureau
|
|
gptkbp:development
|
1960s
1960-1967
|
|
gptkbp:diameter
|
1.5 m
|
|
gptkbp:engine
|
modular design
staged combustion cycle
RD series
RD-0126
|
|
gptkbp:engine_configuration
|
single chamber
|
|
gptkbp:engine_power
|
high efficiency
|
|
gptkbp:engine_type
|
gptkb:Team_Rocket
|
|
gptkbp:environmental_impact
|
low emissions
|
|
gptkbp:first_flight
|
gptkb:1967
|
|
gptkbp:fuel_economy
|
0.5 kg/s
|
|
gptkbp:fuel_mixture_ratio
|
2.5:1
|
|
gptkbp:fuel_type
|
gptkb:RP-1
|
|
gptkbp:historical_significance
|
pioneered liquid propulsion technology
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
RD-0125 engine
|
|
gptkbp:ignition_system
|
multiple
hypergolic
|
|
gptkbp:inspired_by
|
RD-0105 engine
|
|
gptkbp:is_tested_for
|
conducted in 1965
|
|
gptkbp:launch_site
|
gptkb:Baikonur_Cosmodrome
|
|
gptkbp:legacy
|
influenced future designs
|
|
gptkbp:length
|
3.5 m
|
|
gptkbp:manufacturer
|
gptkb:Kuznetsov
|
|
gptkbp:mission
|
gptkb:Soviet_space_program
|
|
gptkbp:number_of_rooms
|
6.5 MPa
|
|
gptkbp:operational_history
|
used in various missions
|
|
gptkbp:operational_use
|
in the 1970s
|
|
gptkbp:oxidation_states
|
gptkb:LOX
liquid oxygen
|
|
gptkbp:propulsion
|
417
kerosene
125 k N
|
|
gptkbp:replaced_by
|
RD-0126 engine
|
|
gptkbp:research_and_development
|
ongoing improvements
|
|
gptkbp:retirement_year
|
gptkb:1980s
|
|
gptkbp:safety_features
|
redundant systems
|
|
gptkbp:specific_impulse
|
300 seconds
|
|
gptkbp:specification
|
available in documentation
|
|
gptkbp:status
|
retired
|
|
gptkbp:successor
|
RD-0126 engine
|
|
gptkbp:type
|
liquid-fueled engine
|
|
gptkbp:used_in
|
gptkb:Soyuz_spacecraft
|
|
gptkbp:weight
|
300 kg
|
|
gptkbp:bfsParent
|
gptkb:RD-0255_engine
|
|
gptkbp:bfsLayer
|
7
|