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gptkbp:instance_of
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gptkb:rocket
|
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gptkbp:bfsLayer
|
5
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gptkbp:bfsParent
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gptkb:Delta_II_7925_H
gptkb:Delta_II_7420-10
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gptkbp:application
|
launch vehicles
|
|
gptkbp:check_in_time
|
150 seconds
|
|
gptkbp:cooling_system
|
regenerative cooling
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|
gptkbp:developer
|
gptkb:Rocketdyne
|
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gptkbp:diameter
|
5.5 ft
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gptkbp:engine
|
gptkb:musical
gptkb:historical_event
1960s
high performance
detailed design
high reliability
Gas-generator cycle
high thrust-to-weight ratio
influenced future designs
liquid bipropellant
single chamber
bell nozzle
proven track record
advanced technology for its time
optimized for missions
RS series
crew launch
part of U. S. space program
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gptkbp:engine_type
|
gptkb:rocket
gptkb:RS-27_A
|
|
gptkbp:first_flight
|
gptkb:1966
|
|
gptkbp:fuel_type
|
RP-1 and Liquid Oxygen
gas-generator cycle
3,200 ° F
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|
https://www.w3.org/2000/01/rdf-schema#label
|
Rocketdyne RS-27
|
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gptkbp:ignition_system
|
hypergolic ignition
|
|
gptkbp:is_tested_for
|
static fire test
|
|
gptkbp:is_used_by
|
gptkb:NASA
|
|
gptkbp:is_used_in
|
gptkb:Saturn_I
|
|
gptkbp:length
|
12.5 ft
|
|
gptkbp:manufacturer
|
gptkb:Rocketdyne
|
|
gptkbp:mission
|
gptkb:Skylab
|
|
gptkbp:number_of_rooms
|
1000 psi
|
|
gptkbp:operational_area
|
gptkb:software
|
|
gptkbp:propulsion
|
gptkb:RP-1
150,000 lbf
83:1
263 seconds in vacuum
150,000 pounds-force
|
|
gptkbp:replaced_by
|
gptkb:RS-27_A
|
|
gptkbp:social_structure
|
Liquid Oxygen
|
|
gptkbp:status
|
retired
|
|
gptkbp:used_in
|
gptkb:Saturn_IB
|
|
gptkbp:weight
|
1,800 lb
|