Apollo Saturn Manual do Utilizador descarregar pdf (Página 41)

S-IC STAGE STRUCTURE

The S-IC stage is approximately 138 feet lo-g and 33 feet in diameter and

is powered by fiv_ liquid-iuei_d Rocketdyn_ F-I engines which generate a nominal

thrust of 7,610,000 pounds. StaI_e engines a;'e supplied by a hi--propellant system

of liquid oxygen (LOX) as the oxidizer and i_-i as the fuel.

The Fo1_ard £kirt

The Forward Skirt accommodates the forward _,ibilical plate, the electrical

and _lectronic canisters, and the venting of the LOX tank and interstage cavity.

The aluminum skin panels are stiffened by ring frames and stringers.

The Oxidizer Tank

! The 343,600 gallon capacity LOX tank is the strucLural link between the

forward and intertank sections. Stiffened by machined "T" stiffeners the tank

is internally equipped with ring baffles for additional stability as well _b £o

reduce IOX sloshing and to provide support for four helium bottles.

The Intertank Section

The intertank section provides structural continuity between the _ and

RP-I tanks.

The RP-I (Fuel) Tank

The RP-I fuel tank, located between the thrust structure and the intertank

section, is a cylindrical aluminum structure with a capacity of 218,900 gallons.

Antislosh ring baffles are located on the inner walls while cruciform baffles

a_e located on the _ower bulkhead. A lightweight foam material, bonded to the

= lower bulkhead, serves as an exclusive rise to minimize unusable residual fuel.

The Thrust Structure

The _hrust structure provides support for the five engines, the base heat

shield, engine falrings and fins, propellant lines, retro rockets and environ-

mental co,_trol ducts. The lower thrust ring also has four-holddown points to

restrain the vehicle, as necessary, from liftlng off at full F-I engine thrust.

P_ogo Sup ress_on

The longitudinal o_cillation in the LV, or "Pogo" effect as it has been ,-

called, has been supressed by utilizing the iOX prevalve cavities in _he fou__[

; outboard englnes as surge chambers. Each of the four cavities is pressurized

with gaseous helium (GHe) at T -Ii minutes from ground supply. Initial fill is

: closely monitored using liquid level resistance thermometers. Ground fill main-

rains cavity pressure until umbillcal disconnect after whlch pressure is main-

talned by the cold helium sphere_ in the LOX tank. Pressure readings are

. transmltted via telemetry to ground monitors during flight.

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Apollo Saturn Manual do Utilizador Página 41