|
gptkbp:instance_of
|
gptkb:rocket
|
|
gptkbp:bfsLayer
|
4
|
|
gptkbp:bfsParent
|
gptkb:RD-0110_engine
gptkb:Buran
gptkb:Buran_spacecraft
|
|
gptkbp:application
|
launch vehicles
|
|
gptkbp:benefits
|
successful development and deployment
|
|
gptkbp:challenges
|
thermal management
|
|
gptkbp:check_in_time
|
300 seconds
|
|
gptkbp:collaborations
|
international space agencies
|
|
gptkbp:controls
|
digital control system
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:debut_year
|
gptkb:1985
|
|
gptkbp:design
|
thermodynamics and fluid dynamics
|
|
gptkbp:designed_by
|
gptkb:Moscow_Institute_of_Thermal_Technology
|
|
gptkbp:developer
|
gptkb:1970
gptkb:1985
engineers and scientists
|
|
gptkbp:diameter
|
2.5 m
|
|
gptkbp:emissions_standard
|
bell nozzle
|
|
gptkbp:engine
|
staged combustion cycle
single engine
single nozzle
modular assembly process
2000 seconds
|
|
gptkbp:environment
|
gptkb:spacecraft
|
|
gptkbp:facilities
|
dedicated test facilities
|
|
gptkbp:features
|
modular design
|
|
gptkbp:first_flight
|
gptkb:1987
|
|
gptkbp:fuel_capacity
|
high
|
|
gptkbp:fuel_type
|
gptkb:RP-1
staged combustion
kerosene
cryogenic storage tanks
|
|
gptkbp:has_documentation
|
available for research purposes
|
|
gptkbp:historical_significance
|
first use in heavy-lift launch vehicles
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
RD-0120
|
|
gptkbp:ignition_system
|
hypergolic
|
|
gptkbp:innovation
|
improved thrust-to-weight ratio
|
|
gptkbp:invention
|
multiple patents filed
|
|
gptkbp:is_tested_for
|
gptkb:Gromov_Flight_Research_Institute
extensive ground testing
|
|
gptkbp:launch_site
|
gptkb:Baikonur_Cosmodrome
|
|
gptkbp:legacy
|
influenced future rocket designs
|
|
gptkbp:length
|
8.5 m
|
|
gptkbp:manufacturer
|
gptkb:Kuznetsov_Design_Bureau
|
|
gptkbp:material
|
high-temperature alloys
|
|
gptkbp:number_of_rooms
|
15 M Pa
|
|
gptkbp:operational_area
|
manned space missions
|
|
gptkbp:project
|
15 years
RD-0120 project
|
|
gptkbp:propulsion
|
300 seconds
liquid oxygen and kerosene
1800 k N
|
|
gptkbp:receives_funding_from
|
gptkb:Monarch
|
|
gptkbp:research_focus
|
gptkb:advanced_propulsion_systems
|
|
gptkbp:safety_record
|
high safety standards
|
|
gptkbp:social_structure
|
gptkb:LOX
liquid oxygen
|
|
gptkbp:status
|
retired
|
|
gptkbp:successor
|
gptkb:RD-0124
|
|
gptkbp:type
|
liquid-fueled
|
|
gptkbp:used_in
|
gptkb:Energia_rocket
|
|
gptkbp:weight
|
3000 kg
|