|
gptkbp:instance_of
|
gptkb:rocket
|
|
gptkbp:application
|
satellite launches
|
|
gptkbp:average_temperature
|
-253 to 650 ° C
|
|
gptkbp:controls
|
digital
|
|
gptkbp:debut_year
|
over 80 launches
|
|
gptkbp:design
|
staged combustion cycle
|
|
gptkbp:developer
|
1990s
|
|
gptkbp:diameter
|
2.4 m
|
|
gptkbp:emissions_standard
|
bell nozzle
|
|
gptkbp:engine
|
modular
staged combustion
|
|
gptkbp:engine_type
|
gptkb:rocket
|
|
gptkbp:first_flight
|
gptkb:2000
|
|
gptkbp:first_introduced
|
gptkb:2000_Atlas_V
|
|
gptkbp:fuel_type
|
gptkb:RP-1
gptkb:item
RP-1 and Liquid Oxygen
turbopump
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
Rocketdyne RD-180
|
|
gptkbp:ignition_system
|
pyrotechnic
|
|
gptkbp:launch_site
|
gptkb:United_Launch_Alliance
|
|
gptkbp:length
|
4.5 m
|
|
gptkbp:manufacturer
|
gptkb:Aerojet_Rocketdyne
|
|
gptkbp:notable_feature
|
dual engine configuration
|
|
gptkbp:number_of_rooms
|
two
2,500 psi
|
|
gptkbp:operational_status
|
in use
|
|
gptkbp:origin
|
gptkb:United_States
|
|
gptkbp:propulsion
|
gptkb:battle
311 seconds
400,000 lbf
|
|
gptkbp:reliability
|
high
|
|
gptkbp:social_structure
|
liquid oxygen
|
|
gptkbp:succeeded_by
|
100%
|
|
gptkbp:used_in
|
gptkb:2022
gptkb:Atlas_V
|
|
gptkbp:weight
|
1,200 kg
|
|
gptkbp:bfsParent
|
gptkb:Atlas_LV-3_B
gptkb:Titan_3_B
|
|
gptkbp:bfsLayer
|
5
|