|
gptkbp:instance_of
|
gptkb:rocket
|
|
gptkbp:bfsLayer
|
6
|
|
gptkbp:bfsParent
|
gptkb:Progress_M-67_M
|
|
gptkbp:aircraft_operated
|
gptkb:Soyuz-2
|
|
gptkbp:application
|
launch vehicles
|
|
gptkbp:artistic_influence
|
influenced other rocket engines
|
|
gptkbp:check_in_time
|
150 seconds
|
|
gptkbp:collaborations
|
used in international missions
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:debut_year
|
multiple launches since 1967
|
|
gptkbp:designed_by
|
gptkb:Kuznetsov_Design_Bureau
|
|
gptkbp:developer
|
gptkb:Monarch
5 years
|
|
gptkbp:emissions_standard
|
converging-diverging nozzle
|
|
gptkbp:engine
|
twin-engine
electric starter
staged combustion cycle
controlled shutdown
|
|
gptkbp:engine_type
|
gptkb:rocket
|
|
gptkbp:environmental_impact
|
low emissions
|
|
gptkbp:features
|
modular design
|
|
gptkbp:first_flight
|
gptkb:1967
|
|
gptkbp:fuel_capacity
|
high efficiency
|
|
gptkbp:fuel_type
|
staged combustion
kerosene
|
|
gptkbp:future_plans
|
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 M Pa
|
|
gptkbp:is_tested_for
|
static fire tests
|
|
gptkbp:legacy
|
proven technology
|
|
gptkbp:manufacturer
|
gptkb:Kuznetsov_Design_Bureau
|
|
gptkbp:market
|
cost-effective
|
|
gptkbp:number_of_rooms
|
two
single combustion chamber
|
|
gptkbp:operational_area
|
crew and cargo missions
|
|
gptkbp:performance
|
high reliability
|
|
gptkbp:propulsion
|
300 seconds
100 k N
333:1
|
|
gptkbp:replaced_by
|
gptkb:RD-0124
|
|
gptkbp:research_and_development
|
ongoing improvements
|
|
gptkbp:safety_record
|
excellent safety record
|
|
gptkbp:social_structure
|
liquid oxygen
|
|
gptkbp:status
|
in service
|
|
gptkbp:type
|
liquid-fueled
|
|
gptkbp:used_in
|
gptkb:spacecraft
|
|
gptkbp:water_source
|
0.5 kg/s
1.0 kg/s
|
|
gptkbp:weight
|
300 kg
|