|
gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:application
|
gptkb:Space_Launch_System
|
|
gptkbp:check_in_time
|
150 seconds
|
|
gptkbp:combustor_type
|
staged combustion
|
|
gptkbp:competitors
|
gptkb:Space_X_Falcon_9
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:design
|
Northrop Grumman engineers
|
|
gptkbp:design_philosophy
|
modular design
|
|
gptkbp:design_purpose
|
cost-effective
|
|
gptkbp:development
|
gptkb:Aerojet_Rocketdyne
gptkb:United_States
|
|
gptkbp:development_cost
|
$1 billion
|
|
gptkbp:engine
|
closed cycle
|
|
gptkbp:engine_configuration
|
twin-engine
vertical
|
|
gptkbp:environmental_impact
|
low emissions
|
|
gptkbp:first_flight
|
gptkb:2021
|
|
gptkbp:fuel_capacity
|
12 m
3.5 m
20,000 kg
|
|
gptkbp:fuel_economy
|
high
|
|
gptkbp:fuel_type
|
RP-1 and liquid oxygen
|
|
gptkbp:has_programs
|
gptkb:National_Security_Space_Launch
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
Northrop Grumman Omeg A engine
|
|
gptkbp:ignition_system
|
pyrotechnic
|
|
gptkbp:investment
|
2000 psi
|
|
gptkbp:is_tested_for
|
gptkb:NASA_Stennis_Space_Center
completed
static fire tests
|
|
gptkbp:launch_date
|
up to 12 launches per year
|
|
gptkbp:launch_price
|
$100 million
|
|
gptkbp:launch_site
|
gptkb:Cape_Canaveral_Space_Force_Station
|
|
gptkbp:launch_vehicle
|
Omeg A family
|
|
gptkbp:lifespan
|
10 years
|
|
gptkbp:manufacturer
|
gptkb:Northrop_Grumman
|
|
gptkbp:market_segment
|
commercial and military
|
|
gptkbp:market_share
|
20%
|
|
gptkbp:number_of_engines
|
2
|
|
gptkbp:operational_status
|
retired
|
|
gptkbp:payload_capacity
|
up to 10,000 kg to LEO
|
|
gptkbp:projected_operational_date
|
2025
|
|
gptkbp:propulsion
|
500,000 lbf
|
|
gptkbp:reliability
|
high
|
|
gptkbp:safety_features
|
redundant systems
|
|
gptkbp:specific_impulse
|
300 seconds
|
|
gptkbp:target_payload
|
up to 5,000 kg to GTO
|
|
gptkbp:type
|
gptkb:Team_Rocket
|
|
gptkbp:used_in
|
Omeg A rocket
|
|
gptkbp:bfsParent
|
gptkb:AR1_rocket_engine
|
|
gptkbp:bfsLayer
|
6
|