Statements (26)
| Predicate | Object |
|---|---|
| gptkbp:instanceOf |
gptkb:piston_engine
|
| gptkbp:burnTime |
approx. 6 minutes
|
| gptkbp:countryOfOrigin |
gptkb:United_States
|
| gptkbp:diameter |
10.1 meters
|
| gptkbp:emptyWeight |
36,600 kg
|
| gptkbp:engine |
5 J-2 engines
|
| gptkbp:firstFlight |
1967
|
| gptkbp:guidanceSystem |
inertial guidance
|
| gptkbp:length |
24.9 meters
|
| gptkbp:manufacturer |
gptkb:North_American_Aviation
|
| gptkbp:massFullyFueled |
481,300 kg
|
| gptkbp:material |
gptkb:aluminum_alloy
|
| gptkbp:numberOfStages |
second stage
|
| gptkbp:propulsion |
liquid oxygen
liquid hydrogen |
| gptkbp:separationMethod |
interstage ring with retro-rockets
|
| gptkbp:thrust |
5 x 1,033 kN
|
| gptkbp:usedIn |
gptkb:Apollo_11
gptkb:Apollo_6 gptkb:Apollo_4 gptkb:Apollo_8 |
| gptkbp:usedOn |
gptkb:Saturn_V
Saturn INT-21 |
| gptkbp:bfsParent |
gptkb:High_Level_Test_Stand_B-II
|
| gptkbp:bfsLayer |
8
|
| http://www.w3.org/2000/01/rdf-schema#label |
Saturn V S-II stage
|