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gptkbp:instanceOf
|
gptkb:satellite
|
|
gptkbp:attachedTo
|
gptkb:satellite
|
|
gptkbp:contains
|
gptkb:Service_Propulsion_System
reaction control system
fuel cells
cryogenic tanks
|
|
gptkbp:countryOfOrigin
|
gptkb:United_States
|
|
gptkbp:diameter
|
3.9 meters
|
|
gptkbp:engineType
|
gptkb:AJ10-137
|
|
gptkbp:firstFlight
|
gptkb:Apollo_4
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
Apollo Service Module
|
|
gptkbp:lastFlight
|
gptkb:Apollo–Soyuz_Test_Project
|
|
gptkbp:launched
|
gptkb:Saturn_IB
gptkb:Saturn_V
|
|
gptkbp:length
|
7.6 meters
|
|
gptkbp:mainEngineThrust
|
91 kN
|
|
gptkbp:manufacturer
|
gptkb:North_American_Aviation
|
|
gptkbp:mass
|
24,520 kg (fully fueled)
|
|
gptkbp:nickname
|
SM
|
|
gptkbp:operatesIn
|
1966
1975
|
|
gptkbp:partOf
|
gptkb:Apollo_spacecraft
|
|
gptkbp:provides
|
gptkb:water
oxygen
propulsion
electrical power
|
|
gptkbp:separatedBefore
|
Earth reentry
|
|
gptkbp:separates
|
Command Module
|
|
gptkbp:usedIn
|
gptkb:Apollo_program
gptkb:Skylab_program
|
|
gptkbp:bfsParent
|
gptkb:Service_Propulsion_System
gptkb:Aerozine_50
gptkb:Apollo_program_hardware
|
|
gptkbp:bfsLayer
|
5
|