Propellant Tanks Pressurization And Venting
VENT amp RELIEF VALVE 41.0-45.0 PSIA LIQUID HYDROGEN niMiiiiiri LIQUID OXYGEN GASEOUS OXYGEN SENSE LINE VENT amp RELIEF VALVE 41.0-45.0 PSIA LIQUID HYDROGEN niMiiiiiri LIQUID OXYGEN GASEOUS OXYGEN SENSE LINE pressure through operation of solenoid valves in the lox tank pressure control module 5 . In this manner, lox tank pressurization is maintained during all engine burn periods. An S-IVB lox tank pressure reading becomes available in the command module CM at S-II S-IVB separation. This...
General Description
SA TURN V SYSTEM DESCRIPTION 1-1 LA UNCH VEHICLE DESCRIPTION 1-3 RANGE SAFETY AND INSTRUMENTA TION 1-3 L V MONITORING AND CONTR OL 1-9 PERCEPTIBLE PRELAUNCH EVENTS 1-12 The Saturn V system in its broadest scope includes conceptual development, design, manufacture, transportation, assembly, test, and launch. The primary mission of the Saturn V launch vehicle, three-stage-to-escape boost launch of an Apollo Spacecraft, established the basic concept. This mission includes a suborbital start of the...
Laminated Honeycomb Sandwich
Attached to the inner surface of the cylinder are cold plates which serve both as mounting structure and thermal conditioning units for the electrical electronic equipment. Mounting the electrical electronic equipment around the inner circumference of the IU leaves the center of the unit open to accommodate the convex upper tank bulkhead of the S-1VB stage and the landing gear of the Lunar Excursion Module LEM . Cross section A of figure 7-3 shows equipment mounting pads bolted and bonded to...
Sivb Aft Skirt Environmental Control
The electrical electronic equipment in the S-IVB forward skirt area is thermally conditioned by a heat transfer subsystem using a circulating coolant for the medium. Principal components of the system, located in the S-IVB stage forward skirt area, are a fluid distribution subsystem and cold plates. The coolant is supplied to the S-IVB by the IU thermoconditioning system starting when electrical power is applied to the vehicle and continuing throughout the mission. For a description of this...
Auxiliary Propulsion System Control Module
modules are detachable and are easily checked or replaced. Each module contains four engines three 150-pound thrust control engines figure 6-15 and one 70-pound thrust ullage engine figure 6-16 . Each module contains its own oxidizer, fuel, and pressurization systems. A positive expulsion propellant feed subsystem is used to ensure that hypergolic propellants are supplied to the engine under zero or random gravity conditions. This subsystem consists of separate fuel and oxidizer propellant tank...
Mobile Launcher
HNgSCU Flow Control Valve Box W Selects either GSCU for operation of one unit while the other recirculates. 2 gt Ground Support Cooling Unit f Supplies water-methanol to the heat exchanger in the IU thermal conditioning system to absorb heat in the IU generated by electronic equipment. p s-IVB Pneumatic Console A amp B r Regulates and controls helium and nitrogen gases for leak testing, functional checkout, propellant loading, purge, and propell ant unloading. As-IVB APS Pneumatic Console y...
Thrust Vector Control
vector forces to position the engine.The deflection rates are proportional to the pitch and yaw steering signals from the flight control computer. Major components of the hydraulic system figure 6-12 are an engine driven hydraulic pump, an electrically driven auxiliary hydraulic pump, two hydraulic 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,...
Sic Stage
INTRODUCTION 4-1 ENVIRONMENTAL CONTROL 4-3 FLIGHT CONTROL SYSTEM____' 4-7 PNEUMA TIC CONTROLS 4-7 The S-IC stage figure 4-1 is a cylindrical booster, 138 feet long and 33 feet in diameter, powered by five liquid propellant F-l rocket engines. These engines develop a nominal sea level thrust of 7,650,000 pounds total, and have a burn time of 150.7 seconds. The stage dry weight is approximately 305,100 pounds and total weight at ground ignition is approximately 4,792,200 pounds. The S-IC stage...
Basic Mission Profile
S-IC, S-II, AND FIRST S-IVB OPERATION 2. COAST IN 100 NAUTICAL MILE EARTH ORBIT 3. CSM SEPARATION FROM S-IVB IU LTA-B DURING FIRST REVOLUTION AND CSM ORBITAL OPERATIONS 4. S-IVB RESTART OVER THE PACIFIC OCEAN DURING SECOND REVOLUTION FIRST INJECTION OPPORTUNITY 5. S-IVB IU LTA-B INJECTED INTO A TYPICAL LUNAR TRANSFER TRAJECTORY 6. S-IVB IU LTA-B MANEUVERS TO A PREDETERMINED ATTITUDE AND EXECUTES RETROGRADE DUMP OF RESIDUAL PROPELLANTS SLINGSHOT PROCEDURE 7. S-IVB STAGE SAFING ACCOMPLISHED ALL...
Emergency Detection And Procedures
EMERGENCY DETECTION SYSTEM 3-1 EMERGENCY DETECTION SYSTEM DISPLA YS . . . . 3-1 EMERGENCY DETECTION SYSTEM CONTROL____ 3-6 ABORT CONTROLS 3-7 ABORT MODES AND LIMITS 3-12 EMERGENCY MODES 3-12 The displays implemented for Emergency Detection System EDS monitoring were selected to present as near as possible those parameters which represent the failures leading to vehicle abort. Whenever possible, the parameter was selected so that it would display total subsystem operation. Manual abort...
Main Display Console Eds Panels
55 56 57 58 59 60 61 62 63 64 65 66 67 69 70 71 72 73 74 75 76 77 78 79 80 81 EDS CSM LM AUTO 1-FINAL SEP-2 EDS CSM LM AUTO 1-FINAL SEP-2 GUIDANCE SI l SI V B U LV STAGE GUIDANCE SI l SI V B U LV STAGE ANGULAR VELOCITY- ATTITUDE ERROR - ALL POLARITIES INDICATE VEHICLE DYNAMICS A signal is sent from the LVDA to activate the LV GUID light Q-52, figure 3-1 in the CM at the same time the flight control commands are inhibited. It is a single cue for abort. Second cues will be provided by the LV RATE...
Holddown Armstail Service Mast
ENGINE HOLDDOWN ARM TAIL SERVICE MAST ORIENTATION ENGINE HOLDDOWN ARM TAIL SERVICE MAST ORIENTATION
Bibliography
Apollo Design Certification Review April 21, 1966 Apollo Program Directive No. 7. Apollo Flight Readiness Reviews, Part I November 8, 1965 Apollo Program Directive No. 8. Apollo Mission Rules April 12, 1967 NASA Management Instruction 8020.9. Apollo Saturn V Facility Description October 1, 1966 K-V-012. Apollo Test Requirements March 1967 NHB 8080.1. Astrionics System Handbook, Saturn Launch Vehicle August 15,1966 Not numbered. Automatic Terminal Countdown Sequence Interlocks SA-502 February...
Mobile Launcher Service Arms
S-IC Intertank preflight . Provides lox fill and drain interfaces. Umbilical withdrawal by pneumatically driven compound parallel linkage device. Arm may be reconnected to vehicle from LCC. Retract time is 8 seconds. Reconnect time is approximately 5 minutes. S-IC Forward preflight . Provides pneumatic, electrical, and air-conditioning interfaces. Umbilical withdrawal by pneumatic disconnect in conjunction with pneumatically driven block and tackle lanyard device. Secondary mechanical system....
Attitude And Ullage Engine Control
to operate the S-IVB stage propellant utilization electronics assembly. The static inverter-converter converts a 28 vdc input into the following outputs 1. 115 vac 400 Hz required to drive propellant utilization valve positioning motors and bridge rebalancing servomotors, 2. 2-vac, peak-to-peak , square wave required to convert propellant utilization error signal to alternating current, 3. 5 vdc required to provide excitation for propellant utilization fine and coarse mass potentiometers, 4....
Power Distribution 1
INSTRUMENTATION PROPELLANT DISPURSION SYSTEM 1 -TELEMETRY - EDS PRESSURIZATION PROPELLANT SYSTEM SEPARATION - PROPELLANT DISPERSION SYSTEM 2 -ELECTRICAL SEQUENCE CONTROLLER -FLIGHT CONTROL _ PROPELLANT LOADING VALVE ANDRELAY POSITION INDICATIONS POWER SYSTEM SWITCHING -ENGINE SYSTEM ENGINE ACTUATION -BATTERY HEATERS - INSTRUMENT HEATERS 5. The recirculation pump motor system is supplied from a 56 volt dc system two 28 volt batteries in series . The division of loads between the main dc bus and...
Sii Engine Actuation
ACCUMULATOR RESERVOIR MANIFOLD ASSEMBLY SERVOACTUATORS SERVOACTUATOR ATTACH POINT SERVOACTUATOR ATTACH POINTS J-2 ENGINE Actuator return fluid is routed to the reservoir which stores hydraulic fluid at sufficient pressure to supply a positive pressure at the main pump inlet. During and following propellant loading, the hydraulic system fluid is intermittently recirculated by the electrically driven auxiliary pump in order to prevent the fluid from freezing. Recirculation is terminated just...
Oxygenhydrogen Burner
518.09 C. G. AT START OF SECOND BURN 518.09 C. G. AT START OF SECOND BURN I j LOX RECIRCULATION FLOW LH2 RECIRCULATION FLOW and the engine hardware for both engine starts is accomplished by separate lox and LH2 chilldown systems. The purpose of the chilldown is to condition the ducting and engine to the proper temperature level, and to eliminate bubbles two-phase flow prior to pressurization. The chilldown, along with the net positive suction head which is obtained by the proper pressure...