|
gptkbp:instance_of
|
gptkb:rocket
|
|
gptkbp:bfsLayer
|
4
|
|
gptkbp:bfsParent
|
gptkb:Proton-M_rocket
|
|
gptkbp:application
|
gptkb:aircraft
|
|
gptkbp:challenges
|
material selection
thrust vector control
combustion stability
engine cooling
|
|
gptkbp:check_in_time
|
150 seconds
|
|
gptkbp:design
|
gptkb:benchmark
reliability
cost-effectiveness
|
|
gptkbp:designed_by
|
OKB-456
|
|
gptkbp:developer
|
gptkb:1955
gptkb:1965
gptkb:Mikhail_Yangel
|
|
gptkbp:diameter
|
1.5 m
|
|
gptkbp:engine
|
staged combustion
single nozzle
|
|
gptkbp:engine_type
|
liquid-fueled
|
|
gptkbp:first_flight
|
gptkb:1965
successful
|
|
gptkbp:fuel_type
|
kerosene
liquid bipropellant
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
RD-0210
|
|
gptkbp:inspired_by
|
RD-0105
|
|
gptkbp:is_tested_for
|
gptkb:Gromov_Flight_Research_Institute
|
|
gptkbp:launched
|
multiple crewed missions
|
|
gptkbp:legacy
|
influenced future engines
|
|
gptkbp:length
|
3.5 m
|
|
gptkbp:mission
|
gptkb:Voskhod_program
gptkb:Vostok_program
gptkb:Soyuz_program
|
|
gptkbp:notable_feature
|
high efficiency
|
|
gptkbp:number_of_rooms
|
6.5 M Pa
|
|
gptkbp:operational_area
|
1965 to 1970s
|
|
gptkbp:origin
|
gptkb:Monarch
|
|
gptkbp:propulsion
|
300 s
100 k N
|
|
gptkbp:replaced_by
|
RD-0211
|
|
gptkbp:social_structure
|
liquid oxygen
|
|
gptkbp:status
|
retired
|
|
gptkbp:successor
|
RD-0211
|
|
gptkbp:technology
|
launch vehicle design
spacecraft propulsion
thrust vectoring
engine testing
staged combustion cycle
liquid propulsion
propellant management
engine integration
rocket staging
|
|
gptkbp:used_in
|
gptkb:spacecraft
|
|
gptkbp:weight
|
200 kg
|