|
gptkbp:instance_of
|
gptkb:rocket
|
|
gptkbp:bfsLayer
|
5
|
|
gptkbp:bfsParent
|
gptkb:The_Angara_Ark
gptkb:Angara_rocket_family
gptkb:Angara_launch
gptkb:Angara_launch_vehicles
gptkb:Angara_rocket
gptkb:Angara_launch_vehicle
gptkb:Angara_A5
gptkb:RD-181
|
|
gptkbp:application
|
gptkb:Angara_rocket
launch vehicles
space launch vehicles
|
|
gptkbp:challenges
|
overcoming initial development hurdles
|
|
gptkbp:check_in_time
|
150 seconds
|
|
gptkbp:collaborations
|
gptkb:NASA
limited
|
|
gptkbp:community_engagement
|
high
|
|
gptkbp:competitors
|
gptkb:RD-0124
gptkb:RD-180
|
|
gptkbp:constructed_in
|
2000s
|
|
gptkbp:controls
|
digital
digital control system
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:debut_year
|
gptkb:2012
|
|
gptkbp:design
|
efficiency and reliability
modular design approach
advanced engineering principles
|
|
gptkbp:designed_by
|
gptkb:Aerojet_Rocketdyne
|
|
gptkbp:developed_by
|
gptkb:RD-0124
gptkb:future_space_missions
gptkb:Kuznetsov_Design_Bureau
gptkb:NPO_Energomash
|
|
gptkbp:developer
|
gptkb:2000
gptkb:2010
$100 million
Kuznetsov engineers
Aerojet Rocketdyne engineers
|
|
gptkbp:diameter
|
2.5 m
1.5 m
|
|
gptkbp:engine
|
gptkb:RD-0124
high efficiency
hypergolic
staged combustion cycle
single nozzle
single shaft
|
|
gptkbp:engine_type
|
gptkb:RD-191_M
|
|
gptkbp:environmental_impact
|
low emissions
|
|
gptkbp:family
|
gptkb:RD_family_of_engines
|
|
gptkbp:features
|
modular design
|
|
gptkbp:feedback
|
positive feedback from users
|
|
gptkbp:first_flight
|
gptkb:2010
gptkb:2014
|
|
gptkbp:fuel_capacity
|
1.5 m
3.5 m
high
|
|
gptkbp:fuel_type
|
gptkb:RP-1
staged combustion
kerosene
3,300 K
|
|
gptkbp:future_plans
|
high potential for upgrades
|
|
gptkbp:has_documentation
|
gptkb:stock_market_index
|
|
gptkbp:has_programs
|
Angara program
|
|
gptkbp:has_single
|
engine variants
|
|
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:park
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:engine
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_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
simulated space conditions
GKNP Ts im. A. M. Isaev
hot fire tests
different fuels
NPO Energomash test facility
|
|
gptkbp:is_used_by
|
gptkb:Russian_space_agency
|
|
gptkbp:is_used_for
|
new technologies
|
|
gptkbp:is_used_in
|
gptkb:Angara_rocket
|
|
gptkbp:launch_date
|
regular launches
|
|
gptkbp:launch_site
|
gptkb:Baikonur_Cosmodrome
gptkb:Russian_space_agency
|
|
gptkbp:launch_vehicle
|
gptkb:Angara
gptkb:Angara_launch_system
commercial launches
|
|
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
|
gptkb:Angara_A5
satellite launches
|
|
gptkbp:number_of_rooms
|
gptkb:musical
single combustion chamber
1800 k Pa
25 M Pa
|
|
gptkbp:operational_area
|
civilian and military missions
commercial launches
|
|
gptkbp:operational_status
|
in service
|
|
gptkbp:origin
|
gptkb:Russia
|
|
gptkbp:partnerships
|
various aerospace companies
|
|
gptkbp:performance
|
high performance
|
|
gptkbp:population_trend
|
increased demand for launch services
|
|
gptkbp:project
|
upgraded versions
|
|
gptkbp:propulsion
|
4.8
300 seconds
1900 k N
191 k N
> 230
|
|
gptkbp:rate_of_fire
|
gptkb:2009
|
|
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:social_structure
|
gptkb:LOX
liquid oxygen
|
|
gptkbp:sparked
|
gptkb:theorem
|
|
gptkbp:status
|
in production
|
|
gptkbp:succeeded_by
|
high
|
|
gptkbp:successor
|
gptkb:RD-180
|
|
gptkbp:training
|
engineer training programs
|
|
gptkbp:type
|
gptkb:rocket
|
|
gptkbp:upgrades
|
planned improvements
|
|
gptkbp:used_in
|
gptkb:Angara_1.2
gptkb:Angara_rocket
gptkb:Angara_A5
|
|
gptkbp:uses
|
liquid oxygen
kerosene
|
|
gptkbp:water_source
|
60 kg/s
120 kg/s
|
|
gptkbp:weight
|
400 kg
800 kg
approximately 800 kg
|