|
gptkbp:instanceOf
|
rocket engine
|
|
gptkbp:application
|
orbital launch
|
|
gptkbp:chemicalFormula
|
Liquid Oxygen
|
|
gptkbp:construction_cost
|
$1 billion
|
|
gptkbp:controls
|
digital
|
|
gptkbp:coolingSystem
|
regenerative cooling
|
|
gptkbp:developer
|
ongoing
|
|
gptkbp:diameter
|
12 ft
|
|
gptkbp:displacement
|
significant in commercial spaceflight.
|
|
gptkbp:engine
|
9
2005-2010
ongoing
180 seconds
modular
iterative
|
|
gptkbp:engineConfiguration
|
clustered
|
|
gptkbp:engineType
|
gptkb:Merlin_1D
liquid-fueled
bell nozzle
|
|
gptkbp:firstFlight
|
2010
June 4, 2010
|
|
gptkbp:fuelType
|
Gas-generator cycle
spark-ignited
RP-1_and_Liquid_Oxygen
|
|
gptkbp:hasArea
|
gptkb:McGregor_Test_Facility
static fire tests
FAA_certified
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
TF-5
|
|
gptkbp:is_designed_to
|
gptkb:SpaceX
|
|
gptkbp:is_used_in
|
gptkb:Falcon_9
|
|
gptkbp:launchSite
|
gptkb:Cape_Canaveral
|
|
gptkbp:launchVehicle
|
gptkb:Falcon_9_Block_1
|
|
gptkbp:length
|
15 ft
|
|
gptkbp:manufacturer
|
gptkb:SpaceX
|
|
gptkbp:missions
|
CRS-1
|
|
gptkbp:operational_status
|
commercial spaceflight
|
|
gptkbp:operationalHistory
|
2010
|
|
gptkbp:performances
|
high
minimal
publicly available
thrust-to-weight ratio
up to 10 flights
optimized for reusability
|
|
gptkbp:propulsion
|
yes
311 seconds
1,500,000 lbf
50:1
|
|
gptkbp:related_engine
|
NASA
Gas-generator cycle
|
|
gptkbp:reliability
|
yes
|
|
gptkbp:status
|
active
|
|
gptkbp:updates
|
ongoing
|
|
gptkbp:weight
|
3,000 lb
|