Saturn rockets were used in support of the Apollo lunar missions, the launch of the Skylab space station, Ferrying crews to and from Skylab, and to launch the American half of the Apollo-Soyuz Test Project.

The United States launched 32 Saturn rockets between 1961 and 1975. The Saturn family of rockets included the Saturn I (10 launches), Saturn IB (9 launches), the three-stage Saturn V (12 launches), and the two-stage Saturn V (1 launch). Although some flights experienced significant problems, no Saturn rocket failed catastrophically in flight.

Thirteen Saturn V rockets flew between November, 1967 and May, 1973. Included were two unmanned test flights, ten manned Apollo missions, and the launch of Skylab.

Saturn V Major Components

S-IC Stage The Saturn V first stage, known as the S-IC stage, was built by the Boeing company. The stage was powered by five F-1 engines. The four outboard engines were hydraulically gimbaled. Propellants were RP-1 and liquid oxygen. Four fairings, located near the base of the rocket, help smooth airflow over the outboard F-1 engines. Each fairing also covered a pair of solid-fueled retrorockets. The retrorockets were fired after main engine cutoff and assisted in separating the spent S-1C stage from the rest of the stack. Photos of S-IC Stage Saturn V S-IC Stage on display at the United States Space and Rocket Center. (Photos: Richard Kruse, 2008) Saturn V S-IC on display at the Kennedy Space Center. (Photos: Kevin Reynolds, 2000)

S-IC / S-II Interstage The interstage was a cylindrical structure mounted between the S-IC and S-II stages. Eight solid fueled ullage motors, located around the perimeter of the interstage, fired after first stage separation. Thrust from the ullage motors forced propellants to settle in their tanks, ensuring pressure in the propellant feed lines. The motors fired for approximately four seconds. Early flights included eight ullage motors. The number was reduced on later missions. Around thirty seconds after first stage separation, explosive charges would be fired, separating the interstage section from the second stage. Photo of an S-IC / S-II Interstage What appears to be a Saturn V Interstage being used as a building at the United States Space and Rocket Center. (Photos: Richard Kruse, 2008)

S-II Stage The Saturn S-II stage was manufactured by North American's Space Division. The stage was powered by five J-2 engines. The four outboard engines were hydraulically gimbaled. A single propellant tank was divided into two compartments by a common bulkhead. The upper compartment would contain liquid hydrogen, while the lower compartment was for liquid oxygen. The S-II stage fired for around six minutes. Photos of S-II Stage Saturn S-II Stage on display at the United States Space and Rocket Center. (Photos: Richard Kruse, 2008) Saturn V S-II on display at the Kennedy Space Center. (Photos: Kevin Reynolds, 2000)

S-IVB aft Interstage Shaped like a truncated cone, the S-IVB aft interstage connected the S-II stage with the S-IVB stage. The interstage included four retrorockets. The forward firing, solid fueled rockets helped ensure a clean separation between the S-IVB and the S-II. Photo of S-IVB aft Interstage What appears to be an S-IVB aft Interstage being used as a building at the United States Space and Rocket Center. (Photos: Richard Kruse, 2008)

S-IVB Stage Developed by McDonnell Douglas, the S-IVB served as third stage for Saturn V rockets. Fueled with liquid hydrogen and liquid oxygen, the S-IVB was powered by a single, restartable, J-2 engine. A single propellant tank was divided into two compartments by a common bulkhead. The upper compartment would contain liquid hydrogen, while the lower compartment was for liquid oxygen. Two solid propellant rocket motors, mounted to the aft skirt, were fired during separation of the second and third stages. Thrust from the motors helped to settle fuel and oxidizer in the main propellant tanks, insuring a safe start for the J-2 engine. On Lunar flights, the S-IVB stage would conduct two burns. First, to put the stage and Apollo spacecraft into a parking orbit. After a period of system checks, the S-IVB would be started a second time. Called a trans-lunar insertion burn, this firing sent the stack on its way to the Moon. Auxiliary Propulsion System (APS) The APS provided attitude control and ullage control for the third stage. The system included two pods, mounted 180 degrees apart on the aft skirt assembly. Each pod included three attitude control engines and a single ullage engine. Each pod included tanks for fuel, oxidizer, and high pressure helium. The attitude control engines provide pitch, roll, and yaw control for the stage. The ullage engines would fire after the first J-2 engine burn to minimize unwanted propellant movement within the tanks. Later, the ullage engines would be used to settle the fuel and oxidizer prior to restarting the main engine. S-IVB Stage Photos Saturn S-IVB Stage on display at the United States Space and Rocket Center. (Photos: Richard Kruse, 2008) Saturn 5 S-IVB stage on display at the Kennedy Space Center. (Photos: Kevin Reynolds, 2000)

Saturn Instrument Unit Designed by NASA and built by IBM, the instrument unit (IU) was located between the S-IVB third stage and the SLA Electronics and electrical equipment located within the IU provided guidance, tracking, and communication services for the rocket. Critical components were mounted on cold plates for cooling. An Environmental Control System (ECS) circulated liquid coolant through the cold plates. On the ground, IU power was supplied by external sources via an umbilical connection. Shortly before launch, power would switch to internal batteries. Four 28v, 350 amp-hour, batteries were included. The IU structure became a load bearing part of the rocket and supported the weight of the Apollo spacecraft above. Instrument Unit Photos Saturn V Instrument Unit on display at the United States Space and Rocket Center. (Photos: Richard Kruse, 2008) Saturn V Instrument Unit on display at the Udvar-Hazy Center. (Photos: Richard Kruse, 2009)

Spacecraft Lunar Module Adaptor (SLA) The spacecraft lunar module adaptor, or SLA, was a tapered section connecting the Instrument Unit with the base of the Apollo service module. The SLA enclosed and protected the lunar module during launch. Saturn SLA Photos Saturn V SLA on display at the Kennedy Space Center. (Photos: Kevin Reynolds, 2000)

Apollo Spacecraft

Apollo CSM and LM Apollo CSM and LM Apollo Command and Service Modules The Apollo command and service module, or CSM, was launched on top of the spacecraft lunar module adaptor. The boost protective cover protected the command module during launch. More information about the Apollo command module. Apollo Lunar Modules The Apollo lunar module, or LM, was stored within the spacecraft lunar module adaptor during launch. More information about the Apollo lunar module.