Statements (55)
| Predicate | Object |
|---|---|
| gptkbp:instance_of |
gptkb:rocket
|
| gptkbp:bfsLayer |
6
|
| gptkbp:bfsParent |
gptkb:RD-180_engine
|
| gptkbp:application |
launch vehicles
|
| gptkbp:average_temperature |
up to 3,000 K
|
| gptkbp:challenges |
overcame several technical challenges during development
|
| gptkbp:check_in_time |
approximately 150 seconds
|
| gptkbp:community_engagement |
high public interest in its performance
|
| gptkbp:community_support |
support from aerospace community
|
| gptkbp:controls |
digital control system
|
| gptkbp:cooling_system |
regenerative cooling
|
| gptkbp:country |
used in international launches
|
| gptkbp:debut_year |
gptkb:2010
multiple successful launches |
| gptkbp:design |
15 launches
|
| gptkbp:developer |
estimated at $200 million
derived from RD-180 engine |
| gptkbp:emissions_standard |
aerospike nozzle
|
| gptkbp:engine |
twin-engine configuration
|
| gptkbp:engine_type |
gptkb:rocket
|
| gptkbp:environmental_impact |
low emissions
|
| gptkbp:facilities |
gptkb:NASA's_Stennis_Space_Center
|
| gptkbp:first_flight |
gptkb:2013
|
| gptkbp:fuel_capacity |
approximately 2.5 meters
high fuel efficiency approximately 4.5 meters |
| gptkbp:fuel_type |
RP-1 and liquid oxygen
gas-generator cycle |
| gptkbp:future_plans |
potential upgrades planned
|
| https://www.w3.org/2000/01/rdf-schema#label |
RD-181 engine
|
| gptkbp:ignition_system |
pyrotechnic ignition system
|
| gptkbp:is_tested_for |
extensive testing conducted
|
| gptkbp:launch_site |
gptkb:Northrop_Grumman
|
| gptkbp:manufacturer |
gptkb:Aerojet_Rocketdyne
multiple component manufacturers involved |
| gptkbp:market |
competitive launch cost
strong market position in launch industry |
| gptkbp:number_of_rooms |
1000 psi
single combustion chamber |
| gptkbp:number_of_stages |
single stage
|
| gptkbp:operational_area |
commercial satellite launches
|
| gptkbp:operational_status |
active
|
| gptkbp:origin |
gptkb:United_States
|
| gptkbp:part_of |
gptkb:Antares_launch_system
|
| gptkbp:partnerships |
collaboration with NASA
|
| gptkbp:propulsion |
300 seconds
180,000 lbf |
| gptkbp:reliability |
high reliability
|
| gptkbp:research_and_development |
ongoing research and development efforts
|
| gptkbp:safety_record |
excellent safety record
|
| gptkbp:specifies |
detailed technical specifications available
|
| gptkbp:succeeded_by |
high success rate
|
| gptkbp:upgrades |
planned future upgrades to enhance performance
|
| gptkbp:used_in |
gptkb:Antares_rocket
|
| gptkbp:weight |
approximately 1,500 kg
|