Lox System Components

Saturn Fill And Drain Diagrams

LEGEND prM(.r , . _ -------- SENSE LINE LOX FILL AND DRAIN INTERTANK UMBILICAL LOX CUTOFF SENSORS (TYPICAL 5 DUCTS) HELIUM BUBBLING IN NO. 1 & 3 INDUCES CIRCULATION BY CAUSING THE LOX IN THESE DUCTS TO RISE THEREBY DRAWING LOX DOWN THROUGH THE OTHER THREE DUCTS. PREPRESSURE ftitzh (HELIUM) 5pu n AFT UMBILICAL NO. 1 LEGEND prM(.r , . _ -------- SENSE LINE

Hazardous Gas Detection Sampling Equipment Layout

Excitation System Layout

The 5-volt measuring voltage supply converts unregulated 28 vdc to a closely regulated 5 ( .005) vdc for use throughout the IU measuring system. This regulated voltage is used primarily as excitation for measurement sensors (transducers), and as a reference voltage for inflight calibration of certain telemetry channels. Like the 56-volt supply, it is basically a dc to dc converter. 20 (with taps for selecting 18 or 19 cells if required to reduce high voltage) Potassium hydroxide (KOH) in...

Saturn Rocket Visor Valves

PRESSURE TRANSDUCER 0-800 PS I RANGE 2 ENGINE NO. 1 GASEOUS HELIUM from the engine back to ground during engine checkout. Approximately 30 seconds prior to the firing command the valve is actuated to the engine position. In this position it directs control fluid to the No. 2 turbopump inlet. An ENGINE POSITION indication is required from this valve prior to, and is interlocked with, forward umbilical disconnect command. Four high voltage igniters, two in the gas generator (GG) body and two in...

Performance

INTRODUCTION 2-1 FLIGHT SEQ UENCE 2-1 FLIGHT PERFORMANCE 2-2 PROPULSION PERFORMANCE 2-13 FLIGHT Saturn V launch vehicle performance characteristics, under the constraints established by environment and mission requirements, are described in this section. Mission profile, variables, requirements and constraints are described in Section X. The SA-503 vehicle will be launched from Launch Complex 39 (LC-39) at the Kennedy Space Center. The flight sequence phases described in the following...

Telemetry Systems

A SUB-CARRIER OSCILLATOR ASSEMBLY (SCO) provides the frequency division multiplexing for the PAM FM FM links. Channels 2 through 15 provide 14 continuous data channels and band X handles the time-division multiplexed data from the model 270 multiplexer. All oscillator outputs are mixed in an amplifier and routed to the FM transmitter in the RF assembly. A model 245 multiplexer increases the number of measurements which may be transmitted over one RF link. The unit permits 80 data measurements...

Saturn V Launch Vehicle

SOLID ULLAGE ROCKET AND RETROROCKET SUMMARY 23,000 POUNDSt 3.75 SECONDS 34,810 POUNDS * 1.52 SECONDS international business machine corp. PRE-LAUNCH LAUNCH VEHICLE GROSS WEIGHT 6,094,073 POUNDS * MINIMUM VACUUM THRUST AT 120 F t AT 170,000 FT. AND 70 F t NOMINAL VACUUM THRUST AT 60 F NOTE THRUST VALUES, WEIGHTS, AND BURN TIMES ARE ALL APPROXIMATIONS. Q BALL TEMPERATURE SENSING S-II AND S-IVB FUEL TANK PRESSURE TRANSDUCER S-IVB ENGINE START ENABLE STAGE ENGINE ACTUATOR COMMANDS STAGE ENGINE...

T rnii

Saturn Thrust Vector Schematic

Each one operates as a 30 x 120 (30 primary channels, each sampled 1 20 times per second) multiplexer with provisions for submultiplexing individual primary channels to form ten subchannels, each sampled at I 2 times per second. Twenty-seven of the 30 primary channels are used for analog data, while the remainaing three are used for references. Ten-channel submultiplexer modules, which plug into the MUX-270, can be use to submultiplex any primary data channel, providing a 10 to 1...

Data Flow Liftoff To Orbital Insertion

Data Flow Satellite

DATA ALSO SENT VIA COMMUNICATIONS SATELLITE AND RELAY STATION Command loads are generated by the real-time computer complex on request of flight controllers. Command loads are based on the latest available telemetry and or trajectory data. Due to the nature of these commands, the data structure cannot be determined prior to the mission but must be calculated as a result of real-time data. A command load, for example, may define the exact conditions under which a thrust may be applied that will...

Mcc Organization

OPERATIONS & PROCEDURES (O& P) MCC MSFN MISSION CONTROL PROCEDURES FLIGHT CONTROL SCHEDULING MANNING CONTROL FORMAT DISPLAYS TELETYPE TRAFFIC ANALYSIS. MS FN CONTROL RADAR AND COMMAND HANDOVERS. MAINTENANCE & OPERATIONS (M& O) MAINTENANCE AND OPERATION OF MCC INSTALLED EQUIPMENT. FLIGHT PLAN DETAILED IMPLEMENTATION. DECISIONS ACT VEHICLE SYSTE AND MCC MSFN IONS ON SPACE IS DYNAMICS OPERATIONS. MONITOR STATUS OF S-IC, S-II, S-IVB FLIGHT SYSTEMS._ MONITOR STATUS OF ELECTRICAL,...

Mission Control Monitoring

Apollo Saturn Schematic

VEHICLE FLIGHT CONTR OL CAPABILITY 9-1 CONTINGENCY PLANNING AND EXECUTION 9-8 VEHICLE FLIGHT CONTROL PARAMETERS 9-19 MANNED SPACE FLIGHT NETWORK 9-20 MSFC SUPPOR T OF LA UNCH AND FLIGHT Mission control monitoring provides, at the various operational levels, the information required to control, direct and evaluate the mission from prelaunch checkout through recovery. The monitoring function during vehicle flight includes space vehicle tracking, receipt and evaluation of flight crew and launch...

Major Events

The S-II stage is brought into the low bay area and positioned on the checkout dolly and access platforms are installed. An insulation leak check, J-2 engine leak check, and propellant level probes electrical checks are made. The S-IVB stage is brought into the low bay area and positioned on the checkout dolly and access platforms are installed. A fuel tank inspection, J-2 engine leak test, hydraulic system leak check, and propellant level sensor electrical checks are made. PHASE BREAKDOWN FOR...

Egress System

Mobil Service Structure Saturn

320' LEVEL (APPROX) 443 FT ABOVE GROUND LEVEL 320' LEVEL (APPROX) 443 FT ABOVE GROUND LEVEL platform. A short pedestal, with a spread footing isolated from the building, provides the mounting surface for the theodolite. These facilities support photographic camera and closed circuit television equipment to provide real-time viewing and photographic documentation coverage. There are six camera sites in the launch pad area, each site containing an access road, five concrete camera pads, a target...

Typical Composite Aerodynamic Heating Indicator Time History

Aerodynamic Pressure Velocity

REPRESENTATIVE OF FLIGHT AZIMUTHS FROM 72 TO 108 MAXIMUM DYNAMIC PRESSURE AERODYNAMIC HEATING INDICATOR DYNAMIC PRESSURE TOTAL ANGLE OF ATTACK. IN RADIANS AERODYNAMIC VELOCITY TIME FROM LIFTOFF TIME OF LIFTOFF 2 - - 3 TIME FROM FIRST MOTION - MINUTES & SECONDS TYPICAL INERTIAL PATH ANGLE DURING BOOST TO PARKING ORBIT TYPICAL INERTIAL HEADING ANGLE DURING BOOST TO PARKING ORBIT TYPICAL INERTIAL VELOCITY DURING TLI BOOST

Lcc Facility Layout

Saturn Launch

Apollo saturn program officer Certain major events may be observed by members of the launch management team who occupy the first four rows in the firing room. The significant launch vehicle events which are displayed on the 10 x 10 foot screen are shown in figure 8-18. The prelaunch sequence of events (see figure 8-19) take place first in the VAB and then at the pad. The VAB events are V-times and are referenced to completion of VAB activities. The pad events are T-times and are referenced to...

Ground Support Interface

LAUNCH COMPLEX 39 8-1 LC-39 FACILITIES AND EQUIPMENT 8-1 VEHICLE ASSEMBL Y AND CHECKOUT 8-16 Launch Complex 39 (LC-39), Kennedy Space Center, Florida, provides all the facilities necessary to the assembly, checkout, and launch of the Apollo Saturn space vehicle. The vehicle assembly building (VAB) provides a controlled environment in which the vehicle is assembled and checked out on a mobile launcher (ML). The space vehicle and the launch structure are then moved as a unit by the...

Saturn V Engines Actuators And Nozzle Arrangement

ALL SIGNAL ARROWS INDICATE POSITIVE VEHICLE MOVEMENTS. 2. VEHICLE PITCHES AROUND THE Y AXIS 3. ENGINE ACTUATOR LAYOUTS SHOWN AS VIEWED FROM AFT END OF VEHICLE. 4. DIRECTIONS AND POLARITIES SHOWN ARE TYPICAL FOR ALL STAGES. 5. + ft INDICATES ENGINE DEFLECTION REQUIRED TO CORRECT FOR POSITIVE VEHICLE MOVEMENT. F NOZZLES ON EXT ACTUATOR EXTENDED Ret ACTUATOR RETRACTED ft THRUST VECTOR ANGULAR DEFLECTION PRELAUNCH VERTICAL ALIGNMENT PENDULUMS The PEA includes the following circuitry 1. Amplifiers,...

Sivb Engine Start

57o O 572.0 574.0 576.0 578.0 580.0 582.0 584.0 GH2 spins LH2 and lox turbopumps causing propellant pressure to buildup. Lox turbopump bypass valve open to control lox pump speed. lox to be injected into thrust chamber. G G valves admit propellants. (Spark ignites propellants causing pressure build up.) OK pressure switches send mainstage OK signal to CM. No. 1 engine out light goes out. (Remaining 4 lights not operative) Engine reaches and maintains 90 thrust or more. GH2 Start tank is...

Sll Engine Cutoff

Saturn Five Fuel

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0 1.1 1.2 Cutoff signal from LVDC triggers 1 valves in pneumatic control package. Pneumatic pressure closes main oxidizer valve Opens oxidizer turbine bypass valve. (Within 10 seconds.) Thrust OK pressure switches sense a decrease in lox pump output pressure, (This event starts time base No. 4). Loss of Thrust could have been the. cause of the cutoff signal T> and have preceeded previous 'efits Helium flow purges oxidizer dome and GG oxidizer...

Guidance Equation

* TERMS DEFINED IN SUBSEQUENT PARAGRAPHS - FLIGHT PROGRAM - POWERED FLIGHT The control subsystem (figure 7-14) is designed to control and maintain vehicle attitude by forming the steering commands used to control the engines of the active stage. Vehicle attitude is achieved by gimbaling the four outboard engines of the S-IC stage, the four outboard engines of the S-1I stage, or the single engine of the S-IVB stage. These engines are gimbaled by hydraulic actuators. Roll attitude control on the...

Propellant Dispersion

PROPELLANT DISPERSION CONTAINER (EBW FIRING UNITS & SAFETY & ARMING DEVICE). to permit charging of the EBW firing units, discharges the storage capacitors in the EBW firing units across the exploding bridgewire in the EBW detonators mounted on the S& A device. The resulting explosive wave propagates through the S& A device inserts to the CDF assemblies and to the CDF tees. The CDF tees, installed on the S-II forward skirt, propagate the wave to two CDF assemblies which detonate to...

Typical Sivb Vehicle Thrust Vs Time History

0 1 2 3 4 5 6 TIME FROM FIRST IGNITION MINUTES Flight loads are dependent on the flight trajectory, associated flight parameters, and wind conditions. These factors are discussed in the following paragraphs. Winds have a significant effect on Saturn V launch vehicle flight loads. Wind criteria used in defining design flight loads for the Saturn V launch vehicle was a scalar wind profile constructed from 95 percentile windiest month speed with 99 percentile shear and a 29.53 feet per second...

Mission Yaribles And Constraints

MISSION FLIGHT PROFILES 10-1 MISSION The mission objectives for the C Prime mission are as follows 1. Verify the LV capability for a free-return, translunar injection TLI . 2. Demonstrate the restart capability of the S-IVB stage. 3. Verify the J-2 engine modifications. 4. Confirm S-II and S-IVB J-2 engine environment. 5. Confirm the LV longitudinal oscillation environment during the S-IC burn period. 6. Verify the lox prevalve accumulators surge chambers incorporated in the S-IC stage to...

Abbreviations And Acronyms

ACE Acceptance Checkout Equipment ACM Actuation Control Module ACN NASA MSFN Station, Ascension Island ACS Attitude Control and Stabilization Systems Force Base AFD Assistant Flight Director AFETR Air Force Eastern Test Range AGAVE Automatic Gimbaled Antenna AGC Apollo Guidance Computer A G COMM Air to Ground and Ground to Air AGCU Apollo Guidance Control Unit ALDS Apollo Launch Data System Modulation amp Ampere or Amplifier AMR Atlantic Missile Range ANG NASA MSFN Station, Antigua ANT DOD-ETR...

Typical Configuration Booster Systems Engineers Console

EVENT INDICATORS S-IC S-II EVENT INDICATOR VEHICLE TELEMETRY STATUS, EDS, COMMAND, RANGE SAFETY EVENT INDICATORS S-IVB GROUND ELAPSED TIME MODULE EVENT INDICATORS GUIDANCE AND NAVIGATION, ATTITUDE CONTROL EVENT INDICATORS GUIDANCE AND NAVIGATION, ATTITUDE CONTROL 19. SUMMARY MESSAGE ENABLE KEYBOARD TYPICAL INFLIGHT CONTINGENCIES REACTIONS Loss of thrust for single control engine No automatic abort Manual abort by LES with two cues Loss of thrust for any single engine No automatic abort Manual...

Lh Systempressurization Flow And Conditioning

Vacuum Jacketed Feed Lines

ENGINE CUTOFF SENSORS 1 AT EACH OF 5 OUTLETS SUPPLIES AN ELECTRICAL INPUT TO PROPELLANT UTILIZATION ELECTRONICS FIG. 5-14 ENGINE CUTOFF SENSORS 1 AT EACH OF 5 OUTLETS COMBUSTION GASES FUEL LH2 GASEOUS HYDROGEN HELIUM He ULLAGE PRESSURE The LH2 feed system furnishes LH2 to the five engines. This system includes five 8-inch vacuum-jacketed feed ducts and five normally open prevalves. The prevalves are closed following tank loading and remain closed until just prior to S-II ignition command. At...

Fl Engine Major Components

Thrust Pressure Switch

TURBOPUMP MAIN FUEL VALVE HEAT EXCHANGER TURBOPUMP MAIN FUEL VALVE HEAT EXCHANGER Range Safety Cutoff has the capability of engine cutoff anytime after liftoff. If it is determined during flight that the vehicle has gone outside the established corridor, the Range Safety Officer will send commands to effect engine cutoff and propellant dispersion. Three thrust OK pressure switches are located on each F-l engine thrust chamber fuel manifold and sense main fuel injection pressure. If the pressure...

Power Distribution

Saturn Retrorocket Separation

OPERATIONAL POWER SYSTEM BATTERY NO. 1 7. Enable outboard engine cutoff. 8. Arm EBW firing unit, retrorockets, and separation system. 9. Fire EBW firing unit, retrorockets, and separation system. In addition, a command from the emergency detection system in the IU can shut down all S-IC stage engines. The S-IC stage instrumentation system figure 4-18 monitors functional operations of stage systems and provides signals for vehicle tracking during the S-IC burn. Prior to liftoff, measurements are...

Sivb Stage

Saturn Aft Skirt

INTRODUCTION 6-1 6-1 ENVIRONMENTAL CONTROL 6-1 6-4 PNEUMA TIC CONTROL 6-17 FLIGHT CONTROL 6-18 A UXILIAR Y PROPULSION SYSTEM 6-20 ELECTRICAL The Saturn S-IVB figure 6-1 is the third booster stage. Its single J-2 engine is designed to boost the payload into a circular orbit on the first burn, then boost the payload to a proper position and velocity for lunar intercept with a second burn. The stage dry weight including interstage is approximately 33,142 pounds. The total weight at ignition is...

Video System

_0PTI CAlT IMAGE gt lliD0_W CRApIr QUARTZ WINDOW OBJECTIVE LENS lt d gt OPTICAL WEDGE CONFINED DETONATING FUSE ASSEMBLY 2 REQUIRED ORDNANCE COWLING FOR RP-1 TANK FLSC CONFINED DETONATING FUSE ASSEMBLY 2 REQUIRED ORDNANCE COWLING FOR RP-1 TANK FLSC The S amp A device figure 4-26 is a remotely controlled electro-mechanical ordnance device that is used to make safe and to arm the S-IC, S-II, and S-IVB stage PDS's. The device can complete and interrupt the explosive train by remote control, provide...

Sii Stage Equipment Locations

Hydrogen Systems Rockets

LIQUID HYDROGEN TANK BULKHEAD 4. INSTRUMENTATION SIGNAL CONDITIONER NO. 2 5. INSTRUMENTATION SIGNAL CONDITIONER NO. 1 8. RADIO COMMAND ANTENNA - 4 PLACES 9. TELEMETRY ANTENNA - 4 PLACES 10. UMBILICAL AND SERVICE CONNECTIONS 12. INSTRUMENTATION SIGNAL CONDITIONER NO. 2 13. INSTRUMENTATION SIGNAL CONDITIONER NO. 3 14. INSTRUMENTATION SIGNAL CONDITIONER NO. 1 15. PROPELLANT MANAGEMENT PACKAGE 16. ELECTRICAL ASSY TIMING AND STAGING CENTER 22. ELECTRICAL POWER...

Typical Angle Of Attack During Tli Boost

The typical propulsion performance data presented herein are based on flight simulations, stage and engine configuration, and static test firing data. A propellant weight summary for each stage is tabulated in figures 2-21 through 2-23. The tables break down propellant use into such categories as usable, unusable, trapped, buildup and holddown, mainstage, thrust decay, and fuel bias. Stage thrust versus time history for the three stages are graphically presented in figures 2-24 through 2-26....

Lox Tank Supply And Vent

RELIEF AND RELIEF VALVE PRESSURE INLET PROPULSIVE VENT The lox fill and drain valve is capable of allowing flow in either direction for fill or drain operations. During tank fill, the valve is capable of flowing 1000 gpm of lox at -297 degrees F at an inlet pressure of 51 psia. Pneumatic pressure for operating the fill and drain valve is supplied by the stage pneumatic control bottle. Loading begins with a precooling flowrate of 500 gpm. When the 5 load level is reached, fast fill 1000 gpm is...

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

Saturn Auxillary Water Pump

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...

Auxiliary Propulsion System Control Module

Propulsion System Quad

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

Thrust Vector Design

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

Saturn Sic Stage Thrust Structure

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

Saturn Flight 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

Saturn Rocket Engine

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...

Mobile Launcher Service Arms

Saturn Second Stage Systems Tunnel

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

System Inputs For Plane

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....

Sii Engine Actuation

Vacuum Jacketed Feed Lines

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

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...