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gptkbp:instance_of
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gptkb:Team_Rocket
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gptkbp:application
|
launch vehicles
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|
gptkbp:check_in_time
|
150 seconds
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|
gptkbp:combustor_type
|
gas-generator cycle
3,200 ° F
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|
gptkbp:cooling_system
|
regenerative cooling
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gptkbp:development
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gptkb:Rocketdyne
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gptkbp:diameter
|
5.5 ft
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gptkbp:engine
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gptkb:historical_significance
1960s
Gas-generator cycle
high thrust-to-weight ratio
influenced future designs
advanced technology for its time
RS series
crew launch
part of U. S. space program
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|
gptkbp:engine_configuration
|
high performance
detailed design
liquid bipropellant
single chamber
|
|
gptkbp:engine_nozzle
|
bell nozzle
|
|
gptkbp:engine_power
|
high reliability
proven track record
optimized for missions
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gptkbp:engine_type
|
gptkb:Team_Rocket
gptkb:RS-27_A
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|
gptkbp:first_flight
|
gptkb:1966
|
|
gptkbp:fuel_type
|
RP-1 and Liquid Oxygen
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
Rocketdyne RS-27
|
|
gptkbp:ignition_system
|
hypergolic ignition
|
|
gptkbp:is_tested_for
|
static fire test
|
|
gptkbp:length
|
12.5 ft
|
|
gptkbp:manufacturer
|
gptkb:Rocketdyne
|
|
gptkbp:mission
|
gptkb:Skylab
|
|
gptkbp:number_of_engines
|
gptkb:1
|
|
gptkbp:number_of_rooms
|
1000 psi
|
|
gptkbp:operational_use
|
gptkb:Apollo_program
|
|
gptkbp:oxidation_states
|
Liquid Oxygen
|
|
gptkbp:propulsion
|
gptkb:RP-1
150,000 lbf
83:1
150,000 pounds-force
|
|
gptkbp:replaced_by
|
gptkb:RS-27_A
|
|
gptkbp:specific_impulse
|
263 seconds in vacuum
|
|
gptkbp:status
|
retired
|
|
gptkbp:used_by
|
gptkb:NASA
|
|
gptkbp:used_in
|
gptkb:Saturn_IB
|
|
gptkbp:used_in_rockets
|
gptkb:Saturn_I
|
|
gptkbp:weight
|
1,800 lb
|
|
gptkbp:bfsParent
|
gptkb:Delta_II_7420-10
|
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gptkbp:bfsLayer
|
5
|