gptkbp:instance_of
|
gptkb:Team_Rocket
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gptkbp:aircraft_operated
|
gptkb:Soyuz-2
|
gptkbp:application
|
launch vehicles
|
gptkbp:check_in_time
|
150 seconds
|
gptkbp:collaboration
|
used in international missions
|
gptkbp:combustor_type
|
staged combustion
|
gptkbp:cooling_system
|
regenerative cooling
|
gptkbp:debut
|
multiple launches since 1967
|
gptkbp:design_features
|
modular design
|
gptkbp:design_influence
|
influenced other rocket engines
|
gptkbp:designed_by
|
gptkb:Kuznetsov_Design_Bureau
|
gptkbp:development
|
gptkb:Soviet_Union
5 years
|
gptkbp:engine
|
electric starter
staged combustion cycle
controlled shutdown
|
gptkbp:engine_configuration
|
twin-engine
|
gptkbp:engine_type
|
gptkb:Team_Rocket
|
gptkbp:environmental_impact
|
low emissions
|
gptkbp:exhaust_system
|
converging-diverging nozzle
|
gptkbp:first_flight
|
gptkb:1967
|
gptkbp:fuel_economy
|
high efficiency
|
gptkbp:fuel_type
|
kerosene
|
gptkbp:future_prospects
|
potential upgrades
|
gptkbp:has_documentation
|
available for engineers
|
https://www.w3.org/2000/01/rdf-schema#label
|
RD-0110 engines
|
gptkbp:ignition_system
|
hypergolic
|
gptkbp:investment
|
10 MPa
|
gptkbp:is_tested_for
|
static fire tests
|
gptkbp:launch_price
|
cost-effective
|
gptkbp:legacy
|
proven technology
|
gptkbp:manufacturer
|
gptkb:Kuznetsov_Design_Bureau
|
gptkbp:number_of_rooms
|
two
single combustion chamber
|
gptkbp:operational_use
|
crew and cargo missions
|
gptkbp:oxidation_states
|
liquid oxygen
|
gptkbp:performance
|
high reliability
|
gptkbp:propulsion
|
100 k N
333:1
|
gptkbp:replaced_by
|
gptkb:RD-0124
|
gptkbp:research_and_development
|
ongoing improvements
|
gptkbp:safety_record
|
excellent safety record
|
gptkbp:specific_impulse
|
300 seconds
|
gptkbp:status
|
in service
|
gptkbp:type
|
liquid-fueled
|
gptkbp:used_in
|
gptkb:Soyuz_spacecraft
|
gptkbp:water_requirement
|
0.5 kg/s
1.0 kg/s
|
gptkbp:weight
|
300 kg
|
gptkbp:bfsParent
|
gptkb:Progress_M-67_M
|
gptkbp:bfsLayer
|
7
|