|
gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:application
|
gptkb:Angara_rocket
launch vehicles
space launch vehicles
|
|
gptkbp:challenges
|
overcoming initial development hurdles
|
|
gptkbp:check_in_time
|
150 seconds
|
|
gptkbp:collaboration
|
gptkb:NASA
limited
|
|
gptkbp:combustor_type
|
staged combustion
3,300 K
|
|
gptkbp:competitors
|
gptkb:RD-0124
gptkb:RD-180
|
|
gptkbp:constructed_in
|
2000s
|
|
gptkbp:control_system
|
digital
digital control system
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:country_of_origin
|
gptkb:Russia
|
|
gptkbp:debut
|
gptkb:2012
|
|
gptkbp:design
|
advanced engineering principles
|
|
gptkbp:design_features
|
modular design
|
|
gptkbp:design_philosophy
|
efficiency and reliability
|
|
gptkbp:designed_by
|
gptkb:Aerojet_Rocketdyne
|
|
gptkbp:developed_by
|
gptkb:RD-0124
gptkb:future_space_missions
gptkb:Kuznetsov_Design_Bureau
gptkb:NPO_Energomash
|
|
gptkbp:development
|
gptkb:2000
gptkb:2010
Kuznetsov engineers
Aerojet Rocketdyne engineers
|
|
gptkbp:development_cost
|
$100 million
|
|
gptkbp:diameter
|
2.5 m
1.5 m
|
|
gptkbp:engine
|
gptkb:RD-0124
hypergolic
staged combustion cycle
|
|
gptkbp:engine_configuration
|
single nozzle
single shaft
|
|
gptkbp:engine_power
|
high efficiency
|
|
gptkbp:engine_type
|
gptkb:RD-191_M
|
|
gptkbp:environmental_impact
|
low emissions
|
|
gptkbp:first_flight
|
gptkb:2010
gptkb:2014
|
|
gptkbp:first_static_fire_test
|
gptkb:2009
|
|
gptkbp:fuel_capacity
|
1.5 m
3.5 m
|
|
gptkbp:fuel_economy
|
high
|
|
gptkbp:fuel_type
|
gptkb:RP-1
kerosene
|
|
gptkbp:future_prospects
|
high potential for upgrades
|
|
gptkbp:has_documentation
|
available
|
|
gptkbp:has_family
|
gptkb:RD_family_of_engines
|
|
gptkbp:has_programs
|
Angara program
|
|
gptkbp:has_single
|
engine variants
|
|
gptkbp:has_thrust
|
191 k N
|
|
gptkbp:historical_event
|
Russian rocketry.
|
|
gptkbp:historical_significance
|
important for Russian space program
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
RD-191
|
|
gptkbp:ignition_system
|
gptkb:spark_plug
hypergolic ignition
|
|
gptkbp:invention
|
multiple patents filed
engine design patents
|
|
gptkbp:is_compatible_with
|
gptkb:Angara_A5
various payloads
|
|
gptkbp:is_considered
|
future upgrades
|
|
gptkbp:is_considered_as
|
reliable engine
|
|
gptkbp:is_designed_for
|
heavy payloads
|
|
gptkbp:is_evaluated_by
|
gptkb:safety_standards
international space agencies
|
|
gptkbp:is_integrated_with
|
launch vehicle systems
|
|
gptkbp:is_known_for
|
high efficiency
|
|
gptkbp:is_optimized_for
|
low-cost launches
|
|
gptkbp:is_part_of
|
gptkb:Russian_space_program
|
|
gptkbp:is_part_of_design
|
modular design approach
|
|
gptkbp:is_part_of_launch_system
|
gptkb:Angara_launch_system
|
|
gptkbp:is_recognized_by
|
aerospace community
|
|
gptkbp:is_supported_by
|
government funding
|
|
gptkbp:is_tested_for
|
gptkb:Khrunichev_State_Research_and_Production_Space_Center
gptkb:Moscow
performance metrics
successful
various conditions
hot fire tests
different fuels
NPO Energomash test facility
GKNPTs im. A. M. Isaev
|
|
gptkbp:is_tested_in_environment
|
simulated space conditions
|
|
gptkbp:is_used_by
|
gptkb:Russian_space_agency
|
|
gptkbp:is_used_in
|
gptkb:Angara_rocket
|
|
gptkbp:is_used_in_development
|
new technologies
|
|
gptkbp:is_used_in_launch
|
commercial launches
|
|
gptkbp:launch_date
|
regular launches
|
|
gptkbp:launch_platform
|
gptkb:Russian_space_agency
|
|
gptkbp:launch_site
|
gptkb:Baikonur_Cosmodrome
|
|
gptkbp:launch_vehicle
|
gptkb:Angara
|
|
gptkbp:legacy
|
part of modern rocket engine history
|
|
gptkbp:length
|
4.5 m
3.5 m
|
|
gptkbp:manufacturer
|
gptkb:Khrunichev_State_Research_and_Production_Space_Center
gptkb:NPO_Energomash
|
|
gptkbp:market
|
commercial space launch
|
|
gptkbp:media_coverage
|
extensive
|
|
gptkbp:mission
|
satellite launches
|
|
gptkbp:notable_mission
|
gptkb:Angara_A5
|
|
gptkbp:number_of_rooms
|
gptkb:1
single combustion chamber
1800 k Pa
25 MPa
|
|
gptkbp:operational_status
|
in service
|
|
gptkbp:operational_use
|
civilian and military missions
commercial launches
|
|
gptkbp:oxidation_states
|
gptkb:LOX
liquid oxygen
|
|
gptkbp:partnerships
|
various aerospace companies
|
|
gptkbp:performance
|
high performance
|
|
gptkbp:project
|
upgraded versions
|
|
gptkbp:propulsion
|
4.8
1900 k N
191 k N
> 230
|
|
gptkbp:public_interest
|
high
|
|
gptkbp:related_to
|
gptkb:NPO_Energomash
|
|
gptkbp:reliability
|
proven
|
|
gptkbp:research_and_development
|
ongoing
ongoing R& D efforts
|
|
gptkbp:safety_features
|
redundant systems
|
|
gptkbp:safety_record
|
excellent
|
|
gptkbp:specific_impulse
|
300 seconds
|
|
gptkbp:staged_combustion
|
gptkb:true
|
|
gptkbp:status
|
in production
|
|
gptkbp:success_rate
|
high
|
|
gptkbp:successor
|
gptkb:RD-180
|
|
gptkbp:training
|
engineer training programs
|
|
gptkbp:trends
|
increased demand for launch services
|
|
gptkbp:type
|
gptkb:Team_Rocket
|
|
gptkbp:upgrades
|
planned improvements
|
|
gptkbp:used_in
|
gptkb:Angara_1.2
gptkb:Angara_rocket
gptkb:Angara_A5
|
|
gptkbp:user_feedback
|
positive feedback from users
|
|
gptkbp:uses
|
liquid oxygen
kerosene
|
|
gptkbp:water_requirement
|
60 kg/s
120 kg/s
|
|
gptkbp:weight
|
400 kg
800 kg
approximately 800 kg
|
|
gptkbp:bfsParent
|
gptkb:Angara_rocket_family
gptkb:Angara_launch
gptkb:Angara_rocket
gptkb:Angara_launch_vehicle
gptkb:Angara_A5
|
|
gptkbp:bfsLayer
|
5
|