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{{Infobox rocket stage
|name = S-II
|image = ap6-MSFC-6758331.jpg
|caption = The [[Apollo 6]] S-II stage during stacking operations in the [[Vehicle Assembly Building|VAB]]
|manufacturer = [[North American Aviation|North American]]
|country = USA
|rockets = [[Saturn V]] (stage 2)<br>[[Saturn INT-21]] (stage 2)
|height = 24.9 m
|alt-height = 82 ft
|diameter = 10 m
|alt-diameter = 33 ft
|mass = 480,900 kg
|alt-mass = 1,060,000 lb
|propmass = 444,000 kg
|alt-propmass = 970,000 lb
|engines = 5 [[J-2 (rocket engine)|J-2]] engine
|thrust = 5,115 kN
|alt-thrust = 1,150,000 lbf
|time = 367 seconds
|fuel = [[Liquid oxygen|LOX]]/[[Liquid hydrogen|LH<sub>2</sub>]]
}}

How it looksసవరించు

S-II
Ap6-MSFC-6758331.jpg
The Apollo 6 S-II stage during stacking operations in the VAB
Manufacturer North American
Country of origin USA
Used on Saturn V (stage 2)
Saturn INT-21 (stage 2)
General Characteristics
Height 24.9 m (82 ft)
Diameter 10 m (33 ft)
Mass 480,900 kg (1,060,000 lb)
Propellant mass 444,000 kg (970,000 lb)
Engine details
Engines 5 J-2 engine
Thrust 5,115 kN
Burn time 367 seconds
Fuel LOX/LH2

See alsoసవరించు