Fuel Containers

Approximately 25-percent of the fuel for the S-I Stage is contained in each of the four fuel containers. The aluminum-alloy containers (Figure 9-6) are cylinders with hemispherical aft bulkheads and torispherical forward bulkheads. The containers have a diameter of 70 inches and a length of 652 inches. The containers are designed to carry flight pressurization and propellant loads due to acceleration. The containers are supported at the aft end by the thrust structure outriggers and at the...

Ordnance Systems

Ordnance systems for the S-IC Stage include retromotors used during S-IC S-n staging, and propellant dispersion system ordnance. Stage Separation System Ordnance. The Stage separation system ordnance consists of eight retromotors located in pairs in each of the four S-IC engine fairings. The motors are mounted at an angle of 6 degrees with the vehicle centerline. Net thrust of the retromotors is equal to or greater than the net thrust of the four outboard F-l engines at the time of first plane...

Stm Stabilized Platform Subsystem

This subsystem is composed of an ST-124M stabilized platform, an electronics box, and the inertial data box. ST-124M Stabilized Platform. The ST-124M stabilized platform is a three gimbal configuration. The inner gimbal or stable element of the platform is maintained in a space fixed orientation utilizing three single-degree of freedom gyroscopes, mounted on the stable element, as inertial sensors to drive servo systems which position the platform yaw, pitch, and roll gimbals. The power to...

Propellant Dispersion System

Each stage of the SATURN I Launch Vehicle includes a propellant dispersion system which is triggered by the stage command system (refer to Paragraph 7-4). Except for component layout, the dispersion systems are identical. S-I Stage. The S-I Stage propellant dispersion system consists of two electronic bridge wire firing units, a safety and arming device with two EBW detonators and primacord initiators, a primacord train, and flexible linear shaped charges (FLSC). Detonation is initiated by a...

Electrical Support Equipment

The electrical support equipment (ESE) is used during checkout, static tests, and launch of the vehicle. The ESE is grouped as follows a. Monitoring and Control Equipment b. System Integration Equipment Figure 18-1. Instrument Unit, SATURN IB With the exception of the monitoring and control equipment and the recording group, MSFC is responsible for fabrication of all of the above. For these two groups MSFC has partial fabrication responsibility. A summary of the ESE functions is given in Table...

Guidance And Control System Interfaces

The guidance and control system has functional interfaces with the APOLLO Spacecraft, electrical support equipment, and the major launch vehicle systems. Those launch vehicle systems interfacing with the guidance and control systems are instrumentation, propulsion, stage separation, emergency detection, vehicle electrical distribution, power distribution and engine gimballing. APOLLO Interfaces. D ring the SATURN IB APOLLO vehicle launch phase, attitude rate information is obtained from the...

Propellant Utilization System

The S-IVB Stage propellant utilization system controls flow of LOX to the engine 3-46 to maintain oxidizer-to-fuel mass ratio between 4 1 and 6 1 and to minimize residual propellants at stage cutoff. In addition, the system performs the following functions a. Supplies the ground loading computer with continuous signals which indicate mass of propellants in the propellant containers. b. Provides signals to the instrumentation system during flight which indicate the mass of propellants remaining....

Aft Skirt And Thrust Structure

The aft skirt and thrust structure are an integral aluminum-alloy assembly. The thrust structure transmits second stage engine thrust loads to the aft skirt. First stage loads and second stage engine thrust loads are transmitted to the LH2 container through the aft skirt. The conical frustum thrust structure transmits the engine thrust loads to the aft skirt. The thrust structure has an aft diameter of 210 inches, a forward diameter of 396 inches and a length of 111 inches. The four outboard...

Ground Support Equipment

The ground support equipment (GSE) is used to transport, protect, handle, service, test, check out, and monitor the complete S-IV Stage, stage assemblies, and stage components. The GSE items are classified as transportation, protection and handling test, checkout, and monitor stage subsystem test, instrumentation* and propellant and gas servicing. Tables 10-3 through 10-7 list the items of each classification along with the item function. Supplies hydraulic fluid to the stage engine hydraulic...

Liquid Oxygen Outboard Containers

Approximately 16-percent of the LOX for the S-I Stage is contained in each of the four outboard containers. Each container Figure 9-5 is a cylinder with hemispherical bulkheads, a diameter of 70 inches, and a length of 678 inches. The aluminum-alloy containers are designed to carry flight pressurization and propellant loads due to acceleration. Each of the outboard LOX containers transmits thrust load from the tail section to the second stage adapter. The containers are supported at the aft end...

Igniter Oxidizer Supply Valve

PRESSURE PROBE 0 TEMPERATURE PROBE PRESSURE PROBE 0 TEMPERATURE PROBE Figure 10-5. RL10A-3 Engine Schematic 1 F ll MC START SOLENOID VAIVi 7 FUll PRESTART HELIUM PRESSURE LOX INLET SHUTOFF VAIVE 7 START SOIENOIO VAIVE START HIIIUM PRESSURE SWITCH INTERSTAGE COOLDOWN. LEID PftgSSUH RELIEF VAtVi DISCHARGE COOIOOWN, RiEEO A PRESSURE RELIEF VALVE

Info

RLlOA-3 Engine Operating Sequence later, energizes the oxidizer prestart solenoid valve which permits control helium 455 25 psi to the actuator of the oxidizer pump inlet shutoff valve. LOX then flows through the LOX pump discharging through the propellant injector. At the end of the prestart cycle the propellant pumps have cooled down to a temperature which will prevent cavitation during pump acceleration. 2. Start Cycle. An electrical signal from the vehicle initiates the start...

Engine Gimbal Hydraulic System

This system illustrated in Figure 23-13, provides thrust vectoring for vehicle flight control of pitch, yaw and roll during first stage powered flight. Thrust vectoring is accomplished by positioning the four outboard gimballed engines through a servo actuator system. Two servo actuators, one in the vehicle pitch axis and one Figure 23-13. Engine-Gimbal Hydraulic System, F-l Figure 23-13. Engine-Gimbal Hydraulic System, F-l in the vehicle yaw axis, are required for each outboard engine. Pitch,...