RD-0210

GPTKB entity

Statements (54)
Predicate Object
gptkbp:instance_of gptkb:Team_Rocket
gptkbp:application gptkb:Space_Launch_System
gptkbp:challenges material selection
thrust vector control
combustion stability
engine cooling
gptkbp:check_in_time 150 seconds
gptkbp:combustor_type liquid bipropellant
gptkbp:country_of_origin gptkb:Soviet_Union
gptkbp:design_purpose gptkb:performance
reliability
cost-effectiveness
gptkbp:designed_by OKB-456
gptkbp:development gptkb:1955
gptkb:1965
gptkb:Mikhail_Yangel
gptkbp:diameter 1.5 m
gptkbp:engine staged combustion
gptkbp:engine_configuration single nozzle
gptkbp:engine_type liquid-fueled
gptkbp:first_flight gptkb:1965
successful
gptkbp:fuel_type kerosene
https://www.w3.org/2000/01/rdf-schema#label RD-0210
gptkbp:inspired_by RD-0105
gptkbp:involved_technology launch vehicle design
spacecraft propulsion
thrust vectoring
engine testing
staged combustion cycle
liquid propulsion
propellant management
engine integration
rocket staging
gptkbp:is_tested_for gptkb:Gromov_Flight_Research_Institute
gptkbp:launches_supported 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 MPa
gptkbp:operational_use 1965 to 1970s
gptkbp:oxidation_states liquid oxygen
gptkbp:propulsion 100 k N
gptkbp:replaced_by RD-0211
gptkbp:specific_impulse 300 s
gptkbp:status retired
gptkbp:successor RD-0211
gptkbp:used_in gptkb:Soyuz_spacecraft
gptkbp:weight 200 kg
gptkbp:bfsParent gptkb:Proton-M
gptkbp:bfsLayer 5