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S-IC

TheApollo 10 S-IC stage is hoisted in theVehicle Assembly Building for stacking
Manufacturer	Boeing
Country of origin	United States
Used on	Saturn V
General characteristics
Height	42 m (138 ft)[1]
Diameter	10 m (33 ft)[1]
Gross mass	2,214 t (4,881,000 lb)[1]
Propellant mass	2,077 t (4,578,000 lb)[1]
Empty mass	137 t (303,000 lb)[1]
Launch history
Status	Retired
Total launches	13
Successes (stage only)	13
First flight	November 9, 1967 (Apollo 4)
Last flight	May 14, 1973 (Skylab 1)
Engine details
Powered by	5 ×F-1
Maximum thrust	34,500 kN (7,750,000 lbf) at sea level[2]
Specific impulse	263 s (2.58 km/s)
Burn time	150 seconds
Propellant	RP-1/LOX

TheS-IC (pronounced S-one-C^[3][4]) was the firststage of the AmericanSaturn V rocket. The S-IC stage was manufactured by theBoeing Company. Like the first stages of mostrockets, more than 90% of the mass at launch was propellant, in this caseRP-1 rocket fuel andliquid oxygen (LOX)oxidizer. It was 42 m (138 ft) tall and 10 m (33 ft) in diameter. The stage provided 34,500 kN (7,750,000 lbf)^[2] of thrust at sea level to get the rocket through the first 61 km (38 mi) of ascent. The stage had fiveF-1 engines in aquincunx arrangement. The center engine was fixed in position, while the four outer engines could behydraulicallygimballed to control the rocket.

TheBoeing Co. was awarded the contract to manufacture the S-IC on December 15, 1961. By this time the general design of the stage had been decided on by the engineers at theMarshall Space Flight Center (MSFC). The main place of manufacture was theMichoud Assembly Facility, New Orleans. Wind tunnel testing took place inSeattle and the machining of the tools needed to build the stages atWichita,Kansas.

MSFC built the first three test stages (S-IC-T, the S-IC-S, and the S-IC-F) and the first two flight models (S-IC-1 and -2).^[5]

It took roughly seven to nine months to build the tanks and 14 months to complete a stage. The first stage built by Boeing was S-IC-D, a test model.^[5]

In addition to the four test stages, NASA ordered 15 flight stages (S-IC-1 through -15) to support the initial Apollo program.^[5] In July 1967, NASA awarded Boeing a contract to begin long-lead-time item acquisition (such as propellant lines and tank components) for the 16th and 17th S-IC stages. A full contract for the construction of S-IC-16 to S-IC-25 was drafted throughout mid-1967, but stages past S-IC-15 were canceled altogether in October of that year due to budgetary restrictions.^[6][7] S-IC-16 to -25 would have been utilized for follow-on Apollo missions, including those from theApollo Applications Program.

The S-IC was composed of five major subsections.

The largest and heaviest single component of the S-IC was the thrust structure, with a mass of 24 short tons (48,000 lb; 22,000 kg).^[1] It was designed to support the thrust of the five engines and redistribute it evenly across the base of the rocket. There were four anchors which held down the rocket as it built thrust. These were among the largest aluminum forgings produced in the U.S. at the time, 4.6 m (15 ft) long and 820 kg (1,800 lb) in weight. The four stabilizing fins withstood a temperature of 1,100 °C (2,000 °F).^[8]

The five F-1 engines were ignited in 3 staggered events, where the center engine was first ignited, followed by two outer engines, and then the remaining two outer engines. These three ignition events were separated by just 300 milliseconds.^[5] This staggered ignition approach lessened the loads on the thrust structure, as an instantaneous ignition of all five engines would impart immense stress on the stage.

Above the thrust structure was the fuel tank, containing 209,000 US gal (790 m³; 27,900 cu ft) of RP-1 fuel.^[8] The tank itself had a mass of over 12 short tons (24,000 lb; 11,000 kg) dry^[1] and could release 1,300 USgal/s (4,900 L/s).Nitrogen was bubbled through the tank before launch to keep the fuel mixed.^[8] During the flight the fuel was pressurized usinghelium, which was stored in tanks in the liquid oxygen tank above. Both the thrust structure and fuel tank had alternating black and white paint, in order to monitor the vehicle'sroll during flight.

Between the fuel and liquid oxygen tanks was the intertank. This contained propellant fill and drain lines for the liquid oxygen tank as well as a portion of the five liquid oxygen feed lines for the engines.

The liquid oxygen tank held 334,500 US gal (1,266 m³; 44,720 cu ft) of LOX. It raised special issues for the designer. The lines through which the LOX ran to the engine had to be straight (as any bend would slow the flow of LOX, which would necessitate even larger and heavier piping) and therefore had to pass through the fuel tank. This meant insulating these lines inside a tunnel to stop fuel freezing to the outside and also meant adding five extra holes in the top of the fuel tank.^[8]

Atop the liquid oxygen tank sat the forward skirt, which connected the S-IC to the S-II stage and contained telemetry equipment and LOX tank vent lines.

Two solid motor retrorockets were located inside each of the four conical engine fairings. At separation of the S-IC from the flight vehicle, the eight retrorockets fired, blowing off removable sections of the fairings forward of the fins, and backing the S-IC away from the flight vehicle as the engines on the S-II stage were ignited.

The propellant tanks of the S-IC were manufactured from 2219-series aluminum panels, while the interstage, forward skirt, and thrust structure were built from 7075-series aluminum. The latter three sections also were corrugated with external stringers, providing additional structural support. The propellant tanks did not feature external stringers, as the tank pressurization provided sufficient rigidity.^[5]

The S-IC also carried theODOP transponder to track the flight after takeoff.

• 
  Cutaway diagram of the S-IC.
• 
  Saturn V first stages S-1C-10, S-1C-11, and S-1C-9 at Michoud Assembly Facility.
• 
  Apollo 11 S-IC separation.

• S-II
• S-IVB
• Apollo (spacecraft)
• MS-IC

Wikimedia Commons has media related toSaturn S-IC.

• Stages to Saturn
• Apollo Saturn Reference Page

• Apollo program
• Rocket stages
• Saturn V

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