Propellant Dispersion System

The S-IC propellant dispersion system (PDS) provides the means of terminating the flight of the Saturn V if it varies beyond the prescribed limits of its flight path or if it becomes a safety hazard during the S-IC boost phase. The system is installed on the stage in compliance with Air Force Eastern Test Range (AFETR) Regulation 127.9 and AFETR Safety Manual 127.1. The PDS is a dual channel, parallel redundant system composed of two segments. The radio frequency segment receives, decodes, and...

Lvdc

The EDS is one element of several crew safety systems. EDS design is a coordinated effort of crew safety personnel from several NASA centers. The EDS senses initial development of conditions which could cause vehicle failure. The EDS reacts to these emergency situations in either of two ways. If breakup of the vehicle is imminent, an automatic abort sequence is initiated. If, however, the emergency condition is developing slowly enough, or is of such a nature that the flight crew can evaluate...

Emergency Egress Systems

The facility provides GH2 at 6,000 paig to the launch vehicle. The facility consists of four storage tanks having a total capacity of 800 cubic feet, a flatbed trailer on which are mounted liquid hydrogen tanks and a liquid-to-gas converter, a transfer line and necessary valves and piping. The azimuth alignment building is located in the approach ramp to the launch structure in the median of the crawlerway about 700 feet from the ML positioning pedestals. The...

Lox Loading And Delivery

As the oxidizer in the bi-propellant propulsion system, lox is contained and delivered through a separate tank and delivery system (figure 4-13). The 345,000 gallon tank is filled through two 6-inch fill and drain lines. Shortly after T-6 hours lox loading begins. Three fill rates are used sequentially a 300 gpm for tank chilldown, a 1500 gpm slow fill rate to stabilize the liquid level and thus prevent structural damage, and a fast fill rate of 10,000 gpm. At approximately 95 full, the rate is...

Launch

The launch pad, figure 8-9, provides a stable foundation for the ML during Apollo Saturn V launch and prelaunch operations and an interface to the ML for ML and vehicle systems. There are presently two pads at LC-39 located approximately three miles from the VAB area. Each launch site is an eight-sided polygon measuring approximately 3,000 feet across. The launch pad is a cellular, reinforced concrete structure with a top elevation of 48 feet above sea level (42 feet above grade elevation). The...

Access Stairway

The ML at the launch pad (at well aa the VAB and refurbish area) is supported by six mount mechanisms which are designed to carry vertical and horizontal loading. Four ) extensible columns, located near each corner of the launcher base exhaust chamber, also support the ML at the launch site. These columns are designed to prevent excessive deflections of the launcher base when the vehicle is fueled and from load -- reversal in case of an abort between engine ignition ami vehicle 1'ftoff. The MSS...

Sic Pneumatic Console Regulates Facility Gases Supplies Operating Pressures To Sic Stage And Sic Pneumatic Checkout

S-IC HYDRAULIC SUPPLY AND CHECKOUT UNIT GIMBALS FOUR OUTBOARD F-l ENGINES KEEPS MAIN LOX VALVES FROM FREEZING CONTROLS F-l ENGINE VALVES The four holddown arms (figure S-7) are mounted on the ML deck 90 degrees apart around the vehicle base. They position and hold the vehicle on the ML during the VAB checkout, movement to the pad and pad checkout. The arm bases have sufficient strength to support the vehicle before launch and to withstand the dynamic loads caused by engine cutoff in an abort...

LIFTOFF

S-IVB Engine GHe Bottle Prssnirization Final SV Telemetry System Chicks S-IVB Turbine Start Bottle Purge S-IVB Engine Thrust Chamber Purge S-IVB Turbine Start Bottle Chilldown S-ll Engine Thrust Chamber Purge GHe Prepare to Launch Test S-IC Fuel Jacket Topping Glycol S-IVB Engine Thrust Chamber Chilldown SI I Engine Thrust Chamber Chilldown S amp A Devices Armed S-IVB Turbine Start Bottle Pressurization Remove Q-ball Cover Retract and Lock CM Access Arm S-ll Turbine Start Bottle Pressurization...

Presaurization System

Plight Control System, Saturn S-1I February 1. 1965 SID 62-140. Flight Dynamics Analysis, Saturn V Launch Vehicle, AS-507 July 24. 1969 Boeing Report D5-lS509 F -7. Flight Manual, Saturn V, SA-506 lune 10, 1969 MSFC-MAN-506. Flight Manual, Saturn V, SA-507 August IS, 1969 MSFC-MAN-507. Flight Operations Planning and Preparation for Manned Orbital Missions John H. Boynton and Christopher C. Kraft, Jr. AIAA Paper No. 66-904. Flight Performance Handbook for Powered Flight Operations Space...

Fuel Tank

The 216,000 gallon fuel tank figure 4-1 provides the load carrying structural link between the thrust structure and intertank structure. The tank is cylindrical, with ellipsoidal upper and lower bulkheads. Antislosh ring baffles are located on the inside wall of the tank and antivortex cruciform baffles are located in the lower bulkhead area. Five lox ducts run from the lox tank, through the RP-1 tank, and terminate at the F-l engines. A lightweight foam filler, which is bonded to the bottom of...

Guidance Switch

The GUIDANCE switch is a two position guarded toggle switch with the two positions being IU and CMC AD-57, figure 3-1 . The switch controls a relay in the IU which selects either the IU or the CMC in the, spacecraft as the source of flight control attitude error signals for. the LV. The normal position of the GUIDANCE switch is IU. Placing the switch in the CMC position permits spacecraft control of the LV under certain conditions. Guidance Reference Failure Condition During the LV burn modes,...

Engine Gimbaling

During the boost and separation phase, the J-2 engine is commanded to the null position to prevent damage by shifting. The engine is also nulled before engine restart to minimize the possibility of contact between the engine bell and the interstage at S-I1 S-1VB separation, and to minimize inertial effects at ignition. The engine is gimbaled figure 6-11 in a 7.0 degrees square pattern by a closed loop hydraulic system. Mechanical feedback from the actuator to the servovalve completes the closed...

Iu Access Door

The structure of the IU consists of three 120-dcgree segments of aluminum ho. cycomh sandwich, joined to form a cylindrical ring. After assembly of the IU, a door assembly provides access to the electronic equipment inside the structure. This access door has been designed to act as a load supporting part of stricture in flight. Work platforms, lights, and air-conditioning are used inside the IU to facilitate vicing operations. When the spacecraft is being fueled through the IU access door, a...

Launch Vehicle Eds Controls Eds Switch

The EDS switch is a two position toggle switch with the two positions being AUTO and OFF Y-58, figure 3-1 . Prior to liftoff the EDS switch is placed in the AUTO position so that an automatic abort will be initiated if 1. a LV structural failure occurs between the IU and the CSM, 2. two or more S-IC engines drop below 90 of rated thrust, 3. LV rates exceed 4 degrees per second in pitch or yaw or 20 degrees per second in roll. The two engine out and LV rate portions of the auto abort system can...

Nasa Communications Networks

The NASA Communications NASCOM network is a point-to-point communications systems connecting the MSFN stations to the MCC. NASCOM is managed by the ioddard Space Flight Center, where the primary communications switching center is located. Three smaller NASCOM switching centers are located at London, Honolulu, and Canberra. Patrick AFB, Florida and Wheeler AFB, Hawaii serve as switching centers for the DOD eastern and western test ranges, respectively. The MSFN stations throughout the world arc...

Recirculation System

Both propellant tanks are pressurized in the same manner by separate systems figures 5-14 and 5-15 . At initiation of prepressurization, the tank vent valves are closed and the disconnect valve and ground prepressurization valves are opened to allow GHe at cryogenic temperatures to flow from the ground source through the prepressurization solenoid valve into the tank pressurization line. This line carries helium into the propellant tank through the tank gas distributor. Propellant recirculation...

Actuators

Ihe flight control computer is an analog computer which converts attitude correction commands 4 and angular change rates 0 into APS thrustcr nozzle and or engine actuatoi positioning commands. Input signals to the flight control computer include I. Attitude correction commands gt from the LVDC LVDA or spacecraft 2. Angular changc rates 40 from the control-KDS rate gyro packagc, via the control signal processor. Since one of the inputs to the flight control computer is from the control-EDS rate...

Oxidizer Tank

The 345,000 gallon lox tank is the structural link between The base heat shield is located at the base of the S-IC stage, forward of the engine gimbal plane. The heat shield provides thermal shielding for critical engine components and base region structural components for the duration of the flight. The heat shield panels are constructed of 15-7 PH stainless steel honeycomb. 1.00-inch thick, brazed to .010 inch steel face sheets. Each outboard F-l engine is protected from aerodynamic loading...

Hazardous Gas Detection

The hazardous gas detection system monitors the atmosphere in the forward skirt and the thrust structure compartment of the S-IC figures 4-2 and 4-3 . This system is not redundant however, large leaks may be detected by propeilant pressure indications displayed in the Launch Control Center. The F-l engine is a single start, 1,530,000 pound fixed thrust, calibrated, bipropellant engine which uses liquid oxygen as the oxidizer and RP-1 as the fuel. Engine features include a bell-shaped thrust...

Helium System

Helium is stored in nine cold helium spheres located in the LH2 tank, eight ambient helium spheres mounted on the thrust structure and one sphere located inside the start bottle on the engine. The nine cold helium spheres supply cold helium for pressurization and repressurization of the lox tank and repressurization of the LH2 tank. Five of the eight ambient helium spheres provide an alternate source of helium for repressurization of the LH2 tank, two provide an alternate source of helium for...

Aft Skirt And Interstage Thermoconditioning

During countdown, air GN2 is supplied by the environmental control system, which is capable of switching from air to GN2 purge. Air or GN2 is supplied at the rate of approximately 3600 scfm. The air purge is initiated when electrical power is applied to the vehicle. GN2 flow is initiated approximately two hours prior to cryogenic loading and continued until liftoff. During periods of hold, GN2 purge is continued. The aft skirt and interstage thermoconditioning and purge subsystem provides the...

Hydraulic Servoactuator

The scryoactuator figure 4-9 is the power control unit for converting electrical command signals and hydraulic power into mechanical outputs to gimbal the engines on the S-ic stage. The flight control computer IU receives inputs from the guidance system in the IU and sends signals to the servoactuators to gimbal the outboard engines in the and magnitude required. An integral mechanical feedback varied by piston position modifies the effect of the iu control signal. A. built-in potentiometer...

Hydraulic System

Major components of the hydraulic system figure 6-12 are an engine driven hydraulic pump, an electrically driven auxiliary hydraulic pump, two nydraulic actuator assemblies, and an accumulator reservoir assembly. The engine driven hydraulic pump is a variable displacement type driven directly from the engine oxidizer turbopump. In normal operation, the pump delivers up to 8 gpm under continuous working pressure. The auxiliary hydraulic pump is an electrically driven pump which is capable of...