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I

ENGINEERING DEPARTMENT

TECHNICAL MANUAL

SDES-64-415

IACCESS10N NUMBER) (THRU)

EGORW

Saturn LAUNCH VEHICLE SA-10

AND LAUNCH COMPLEX 37B FUNCTIONAL SYSTEMS DESCRIPTION

Volume I11 LH2 FUEL SYSTEM FUNCTIONAL DFSCRIPTION,

INDEX O F FINDING NUMBERS, AND GPO PRICE $ MECHANIC AI, SCHEMATICS

OTS PRICE(S) $

4, CHRYSLER PAf CORPORATION SPACE DIVISION

Hard copy (HC)

Microfiche (MF)

https://ntrs.nasa.gov/search.jsp?R=19650013467 2020-07-20T13:41:28+00:00Z

SDFS-64-415

SATURN I LAUNCH VEHICLE SA-10

AND LAUNCH COMPLEX 37B

FUNCTIONAL SYSTEM DESCRIPTION

VOLUME I11

FUNCTIONAL DESCRIPTION, INDEX OF FINDING NUMBERS, AND MECHANICAL SCHEMATICS

LHz FUEL SYSTEM

d

i .AUGUST 1964. -.

CHRYSLER CORPORATION SPACE DIVISION - NEW ORLEANS, LOUISIANA

' 1429-10-8-64

FOREWORD

This volume is one of a se t of eleven volumes that describe mechanical and electro- mechanical systems of the Saturn I, SA-10 launch vehicle and launch complex 37B. The eleven-volume set is prepared for the Functional Integration Section, Systems Integration and Operations Branch, Vehicle Systems Division, P&VE Laboratory, MSFC , by Systems Engineering Branch, Chrysler Corporation Space Division under Contract KAS 8-4016. Volume titles a r e listed below:

Volume I R P - 1 Fuel System

Volume I1 LOX System

Vvlume 111 LH2 Fuel System - Volume IV Nitrogen and Helium Storage Facility

Volume V Pneumatic Distribution System

Volume VI Environmental Conditioning Systems

Volume VI1 Launch Pad Accessories

Volume VI11 H-1 Engine and Hydraulic System

Volume IX RLlOA-3 Engine and Hydraulic System

Volume X Separation and Flight Termination Systems

Volume XI Supplement: Legend and Composite Schematic

The technical content of this volume reflects up-to-date design information available from the S-I/S-IB Project Engineer, R-P&VE on August 7 , 1964.

System mechanical schematics are provided in section 3 to support the functional description of the system. and functional descriptions of components identified on the mechanical schematics.

The index of finding numbers in section 2 provides physical

j i i

a TABLE O F CONTENTS

Section

1

2

3

Figure

1-1

3- 1

3-2

Subject

FUNCTIONAL DESCRIPTION ...................... 1.1 INTRODUCTION ......................... 1 . 2 SYSTEM FUNCTIONS ...................... 1 . 2 . 1 LH2 Storage ............................ 1.2 .2 LH2 Transfer ............................ 1 . 2 . 3 S-IV Stage Propulsion System Supply ............ 1.3 SYSTEM DESCRIPTION ..................... 1.3 .1 Storage Subsystem ........................ 1.3.2 Transfer Subsystem ........................ 1.3.3 Control Subsystem ........................ 1.3.4 S-IV Stage LH2 Subsystem ................... 1.4 SYSTEM OPERATIONS .....................

Page

1.1

1.1

1.1

1.1

1.1

1 . 3

1 . 4

1 . 4

1 .7

1 .8

1.11

1 . 1 3

1 .4 .1 Storage ................................ 1.13

1.4.2 Preparations for LH2 Transfer ................ 1.14

1 .4 .3 Prelaunch LHZ Transfer .................... 1.16

1.4.4 Launch Cancellation ........................ 1 . 2 2

1 .4 .5 S-IV Stage Propulsion System Supply 1 .25

INDEX OF FINDING NUMBERS 2 .1

MECHANICAL SCHEMATICS ...................... 3 . 1

LIST OF ILLUSTRATIONS

Title Page

Launch Vehicle SA-10 and Launch Complex 37B LH2 Fuel System-Block Diagram .......................... 1-29

Launch Complex 37B LH2 Fuel Storage Facility-Mechanical Schematic ................................... 3 . 3

Launch Complex 37B LH2 Transfer Subsystem and S-IV Stage LH2 Subsystem-Mechanical Schematic ............ 3 .5

V

SECTIOX 1

FUN C T ION A L DE SCRIPT I ON

1.1 INTRODUCTION

The LH2 (liquid hydrogen) fuel system a s described in this volume is comprised of equipment on launch complex 37B and launch vehicle equipment within the S-IV stage. The launch complex equipment s tores LH2 for fueling the S-IV stage and, during the launch vehicle countdown, loads the S-IV stage wi th a predetermined quantity of LH2. Launch complex equipment a l so drains LH2 from the stage in the event of a launch cancellation. S-IV stage equipment receives and s tores LH2 supplied from the launch complex and, during vehicle flight. controls the supply of LH2 to the S-IV stage propulsion system. Figure 1-1 identifies system equipment with respect to both location and functional subsystem arrangement.

This section descr ibes major components and subsystems and descr ibes the operation of the system during an abort-free vehicle countdown, launch, and flight. Specifically excluded from the description a r e components and subsystems that function as a re- sult of an abortive malfunction or a re used exclusiveiy for maintenance of launch complex equipment.

1 .2 SYSTEM FUNCTIONS

The LH2 system has three major functions; i t s tores LH2 fo r fueling the S-IV stage, it t r ans fe r s LH2 to and from the S-IV stage, and it controls the supply of LH2 to the S-IV stage propulsion system.

1.2.1 LH2 Storage (F igure 1-1) - The storage of LH2 in the LH2 storage facility involves three operations; storage facility purge, storage tank filling, and storage tank pressurization. Before the storage tank is filled, the tank and storage facility lines are purged with gaseous nitrogen (GN2) to prevent the formation of explosive mixtures of a i r and hydrogen. Following the GN2 purge, the storage tank is purged with gaseous hydrogen (GH2) and filled with LH2 from mobile tankers. Until LH2 transfer operations a r e initiated, the LH2 remains in the storage tank under a pres - su re of approximately 4 psig.

1.2.2 LH2 Transfer (F igure 1-1) - There a r e two types of LH2 transfer operations: prelaunch operations performed to fuel the S-IV stage, and operations performed in the event of a launch cancellation to drain LH2 from the S-IV stage and remove residual LH2 o r GH2 in the t ransfer lines. f e r operations are described in the following paragraphs.

The prelaunch and launch cancellation t rans-

1.2.2.1 Prelaunch Operations. Prelaunch operations include S-IV stage propellant tank assembly and t ransfer line purge, S-IV stage LOX tank pressurizat ion, LH2 storage tank pressurizat ion, transfer line and S-IV stage cooldown, fi l l , replenish, and final topping. These operations are initiated and monitored at the LH2 control

0

1.1

and LH2 components panels in the launch control center (LCC) and a r e jointly controlled by Douglas Aircraf t Company (DAC) and Launch Operations Control ( LOC) propellant loading control equipment in the automatic ground control station (AGCS) . Normally, the operations are sequenced automatically; but, mode selec- tion capabilities at the LH2 control panel allow manual sequencing or simulation of the operations, The S-IV Stage propellant tank assembly and t ransfer lines a r e purged to provide an inert atmosphere within the S-IV stage and the t ransfer line pr ior to LH2 t ransfer . The purge medium is helium (He) supplied f rom valve panel A (volume V) . After passing through the stage and t ransfer l ines, the He is vented to the launch facility burn pond.

The S-IV stage LOX tank is pressurized with He to approximately 48 psig to prevent collapse of the common bulkhead between the LH2 tank and the LOX tank.

The LH2 storage tank is pressurized to provide the p re s su re head necessary for t ransferr ing LH2 from the storage tank to the S-IVstage LH2 tank. Pressurizat ion is accomplished by means of an LH2 vaporizer that warms LH2 drawn from the storage tank and provides gaseous hydrogen (GH2) for tank pressurization. The storage tank pressurization components control GH2 flow into the tank and maintain tank p res su re at approximately 42 psig throughout LH2 t ransfer .

Immediately following storage tank pressurizat ion, cooldown of the t ransfer line and the S-IV stage is initiated. During this operation, LH2 flows, a t a limited r a t e , from the storage tank through the LH2 subcooler and t ransfer line and into the S-IV stage LH2 tank. The LH2 flow precools the t ransfer line and LH2 tank to reduce LH2 vaporization during subsequent LH2 transfer. The cooldown LH2 supply continues to flow until the s-IV stage LH2 tank is 15 percent filled.

When the S-IV stage LH2 tank is 15 percent filled, main fill t ransfer is initiated automatically and LH2 flow from the storage tank to the S-IV stage is increased to approximately 2000 gpm. Main fill continues a t this ra te until the S-IV stage propellant loading control equipment senses that the LH2 tank is 92 percent full. A t this point in the filling operation, the S-IV stage propellant loading control equipment sends a signal that terminates LH2 flow through the main fill valve and initiates the replenish operation.

During replenish, LH2 flows to the S-IV stage through the replenish valve which regulates the LH2 flowrate to either 20 gpm o r 500 gpm. The 500-gpm flow is maintained until the LH2 tank is 99.25 percent filled as indicated by S-IV stage propellant loading control equipment. At this indication, the replenish valve reduces LH2 flow to 20 gpm, which is less than enough to compensate for boiloff losses. When the LH2 tank fuel level falls to the 99-percent-full level, the replenish valve increases LH2 to 500 gpm and maintains this flowrate until the tank is again filled to the 99. 25-percent-full level. The fuel level is repeatedly adjusted between 99.00 and 99.25 percent full until final topping is initiated a t approximately T -140 seconds in the prelaunch countdown.

1.2

During final topping, the LH2 tank is filled to the 100-percent-full level and pressurized. LH2 flow through the replenish valve is increased to, and is maintained a t , 500 gpm until the tank is 100 percent filled. S-IV stage propellant loading control equipment then commands closure of the replenish valve, the S-IV stage fill and drain valve, and LH2 tank vent valves. With closure of the replenish valve, the t r ans fe r line vent valve is opened, and the t ransfer line between the replenish valve and the vehicle is vented to the launch facility burn pond. The S-IV stage LH2 tank is then pressurized with helium routed from valve panel B (volume V) to S-IV stage LH2 tank pressurization components. T -90 seconds.

Final topping is complete a t approximately

At liftoff, all ground connections to the vehicle are released, and the umbilical housings a r e purged with helium.

1.2.2. 2 Launch Cancellation Operations. This group of operations includes LH2 storage tank venting, S-IV stage LH2 tank pressurization, S-IV stage LH2 tank draining, transfer line warmup, and manually controlled GN2 purging of residual GH2 from the transfer line (manual inerting) .

When a launch is cancelled,LH2 transfer to the S-IV stage is halted and the LH2 system is placed in standby status. To prevent further LH2 transfer to the vehicle, the main fill and replenish transfer valves are closed, and the S-IV stage fill and drain valve is closed.

Upon initiation of S-IV stage LH2 drain, the LH2 storage tank pressurization supply is terminated and storage tank pressure is vented to the atmosphere. the S-IV stage LH2 tank vent valves a re closed and the tank is pressurized with helium. When the LH2 tank pressurization is complete, the S-IV stage fill and drain valve, main fill valve and replenish valve are opened. The S-IV stage LH2 tank pressure forces LH2 from the tank, through the transfer line, and into the LH2 storage tank.

Simultaneously,

A s LH2 is drained, t ransfer line temperature is monitored a s a means of detecting LH2 flow. A temperature increase indicates a reduction of LH;! flow resulting f rom depletion of LH2 in the S-IV stage LH2 tank. When an increase in t ransfer line temperature is indicated, the line warmup operation is initiated. storage tank and further S-IV stage LH2 tank pressurization are terminated, and the t ransfer line is vented to the launch facility burn pond. hours to allow complete vaporization of residual LH2 and the dissipation of GH2 vapors. GN2 purge supply to the t ransfer line. GH2 and provides an inert atmosphere within the lines.

LH2 transfer to the

Venting is continued f o r 3

Following line warmup, manual valves are opened to admit a low-pressure The GN2 purge eliminates any remaining

1 . 2 . 3 S-IV Stage Propulsion System Supply - System equipment in the S-IV stage per forms three operations in supplying LH2 to the stage propulsion system; it con- t ro l s LH2 tank pressurization to maintain the structural integrity of the tank and to provide a net positive suction head to the engine turbopumps, it equally distributes LH2 to the six RLlOA-3S engines, and i t monitors fuel depletion and provides fuel

1. 3

m a s s signals used by the S-IV stage propellant utilization system in initiating engine cutoff.

1 . 3 SYSTEM DESCRIPlION

1. 3.1 Storage Subsystem - The major components within the LH2 storage subsystem a r e identified in figure 1-1. below; the remainder a re described in the index of finding numbers, on system mechanical schematics and in descriptions of system operations.

The more complex of these components a r e described

1. 3. 1.1 Pneumatic Control Console ( Figure 3-1). receives 3500-psig G N 2 from the nitrogen and helium storage facility (volume IV) and provides 750- and 25-psig GN2 outputs, operate pneumatic valves in the LH2 storage facility. 'The CN2 is routed to the pneumatic valves through solenoid valves which a re controlled by signals from the launch control center. The 25-psig G N 2 output is used as a reference pressure for several storage facility control devices and is distributed through restrictive orifices for purging lines and electrical equipment cabinets.

The pneumatic control console

The 750psig G N 2 output is used to

1.3. 1.2 Storage Tank Pressurization Components (F igure 3-1). Storage tank pressurization components include an LH2 vaporizer, p ressure controllers, flow regula- t o r s , and other associated control devices. These components maintain storage tank ullage pressure at approximately 4 psig during steady state slorage conditions and increase the pressure to approximately 42 psig during LH2 t ransfer operations, Dur- ing steady-state conditions, storage tank pressurization i s accomplished through controlled venting of LH2 boiloff within the storage tank. During LH2 transfer operations, however, additional tank pressurization is provided by LH2 Vaporizer A3754. The vaporizer receives LH2 from LH2 Storage Tank A3753 and provides GH2 for s torage tank pressurization. Excess pressure is vented to the storage facility burn pond. Major components associated with pressurization control a r e listed and des-

* c ribed below.

a. Flow Regulator A3338 - Maintains storage tank pressure at approximately 4 psig during LH2 storage and storage tank filling operations by controlling the venting of LH2 boiloff. The regulator position is determined by the differential p ressure applied ac ross its actuator.

The actuator receives 25-psig GN2 f rom the pneumatic control console and a varying GN2 supply from Pneumatic Controller A3551. The pneumatic controller increases control pressure f rom 3 to 15 psig as storage tank ullage pressure rises and thereby decreases the differential p re s su re avross the regulator actuator. Regulator position is varied until venting is adjusted to maintain storage tank pressure at approximately 4 psig. When s torage tank pressure exceeds 4 psig, venting control is t ransfer red to main vent Pneumatic Valve A3304.

b. Flow Regulator A3305 - Controls the flow of LH2 to Vaporizer A3754 to maintain storage tank pressure a t 42 psig during LH2 t ransfer operations. Regulator

1 . 4

position is determined by the differential between control p re s su res applied ac ross the regulator actuator. The actuator receives a constant 25-psig GIi2 supply from the pneumatic control console and a varying GE2 supply from Pneumatic Controller A3544.

The pneumatic controller senses storage tank ullage p res su re and varies differential pressure ac ross the regulator to increase o r decrease LH2 flow through the regulator. As storage tank p res su re increases, differential pressure is decreased and LHg flow is reduced. When storage tank pressure reaches 42 psig, the regulator is closed to prevent further pressurization. Should the pneumatic controller malfunction, the regulator can be closed by the action of Solenoid Valve A3387 and P r e s s u r e Switch A3538. If storage tank ullage pressure increases to 55 psig, the p re s su re switch actuates and sends a signal that opens the solenoid valve, The solenoid valve vents control pressure from the regulator actuator and allows the regulator to close.

c. Relief Valve A3640 - Provides overpressure protection for the storage tank vent line by relieving excess pressure a t 100 psig to the storage facility burn pond.

1. 3. 1 . 3 LH2 Subcooler (Figure 3-1). LHz Subcooler A3752 is a tube-in-shell heat

is positioned in the t ransfer line such that all LH2 transfer to and fr 'p" the S-IV stage exchanger that supercools LH2 being transferred to the S-IV stage.

pas ses through i t , but it is functional only during the replenish and final topping operations. Supercooling is required to prevent excessive in-line vaporization of LH2 that would otherwise occur due to the low rate of LH2 transfer during these operations The subcooler shell is filled wi th LH2 drawn from the t ransfer line, and the LH2 being transferred to the S-IV stage passes through a coil of tubes submerged in the LH2 contained in the subcooler shell. Immediately pr ior to initiation of the replenish operation, Vacuum Pump A3751 reduces the subcooler she11 pressure and thereby reduces the temperature of LH2 coolant in the shell. LH2 flowing through the trans- f e r line passes through the tube side of the subcooler and is supercooled to approximately -426 F. Other components functionally associated with subcooler operation are described below:

0

a. Liquid Level Probe A3509 continuously monitors the LH2 level within the subcooler shell and provides control pressure f o r rr\gulating LH2 flow into the shell. The probe is mounted on top of the subcooler and extends down- ward between the inner wall of the subcooler and the t ransfer tubes. probe is sealed at the bottom, and the upper end is connected to a pressure- tight chamber that is pressurized to 45 psig with GE2.

The

Chamber p re s su re drops as the LH2 level rises and increases as the LH2 level drops. Thus, the chamber pressure is indicative of the LH2 level and is used as a control pressure for regulating the flow of LH2 to the subcooler shell.

1 . 5

Two capacitance-type, point-level s enso r s , mounted near the bottom of the probe, sense the LH2 level and send signals to transducer cabinet indicators for local monitoring of the LH2 level. Level Sensor A3511 provides a high level indication when submerged in LH2 and Liquid Level Sensor A3512 provides a low level indication when the LH2 level recedes below it. Liquid Level Sensor A3511 is also electrically interlocked with Solenoid Valve A3386. Actuation of Solenoid Valve A3386 closes subcooler inlet Flow Regulator A3309. and shuts off LH2 flow into the subcooler shell.

b. Pneumatic Controller A3513 and Flow Regulator A3309 function together to maintain a constant LH2 level within the subcooler. The controller senses pressure variations in Liquid Level Probe A3509 and provides proportional increases o r decreases in control p re s su re applied to the flow regulator. The flow regulator controls LH2 flow from the transfer line into the subcooler. The controller receives a 25-psig G N 2 supply from the pneumatic control console and regulates control pressure applied to the flow regulator between 3 and 15 psig. An increase in LH2 level reduces the controller output p re s - sure . The reduced output pressure increases differential p re s su re applied ac ross the flow regulator actuator and thereby reduces LH2 flow through the flow regulator. the differential p re s su re applied to the flow regulator, thereby increasing LH2 flow through the regulator. level are compensated for by LH2 flow regulation through the flow regulator.

A decrease in LH2 level causes a corresponding decrease in

Thus, increases or decreases in LH2 coolant

c. Pneumatic Controllers A3515 and A3514 provide an alternate means for controlling the LII2 level adjustments through F l o ~ Regulator A3309. These two controllers substitute for Pneumatic Controller A3513 and Liquid Level Probe A3509, which can be isolated by closing Manual Valve A3412. Controller A3515 sepses subcooler LH2 level and regulates control p re s su re applied to Pneumatic Controller A3514 which, in turn, regulates the positioning of Flow Regulator A3309. Pneumatic Controller A3515 senbes LH2 level by sensing the differential pressure between the upper and lower taps on the subcooler shell. Upper-tap p re s su re is applied to the pneumatic controller through Manual Valves A3384 and A3406, and lower-tap p res su re is applied through Manual Valves A3385 and A3407. tial pressure, Pneumatic Controller A3515 reduces a 25-psig GN2 supply from the pneumatic control console and prokides a 15- to 3-psig control pressu re for control of Pneumatic Controller A3514. Pneumatic Controller A3514 also receives a 25-psig GN2 input f rom the pneumatic control console and, in proportion to the control pressure 3pplied from Pneumatic Controller A3515, applies a 3- to 15-psig control pressurr’ to Flow Regulator A3309.

Pneumatic

In proportion to the applied differen-

d. Flow Regulator A3342 regulates c;!~. , Y flow from the subcooler to Vacuum Pump A3751 during vacuum pump operation to maintain a se t subcooler shell pressure. pneumatic console and a vari:ible control p re s su re of 3- to 15-psig GN2 from Pneumatic Controller A3554. determines the regulator position.

The flow regulator receives 25-psig G K ~ control p re s su re f rom the

The differential between these control p re s su res

1. G

e.

f.

g.

h.

i.

j.

1. 3 . 2

The pneumatic controller actuator s enses , a s control p re s su re , subcooler . shell p ressure over a range of 0 to 15 psig. In proportion to the applied shell p re s su re , the pneumatic controller reduces 25-psig G N 2 from the pneumatic control console to a 3- to 15- psig control pressure for positioning Flow Regulator A3342. A s Vacuum Pump A3751 reduces the subcooler shell p res - s u r e , the control pressure applied to the flow regulator is reduced, thereby reducing GH2 flow through the flow regulator. Conversely, an increase in subcooler shell p ressure causes an increase in GH2 flow through the flow regulator.

Temperature Probe A3585 and Temperature Indicator A3584 provide local monitoring of vacuum line temperature.

Temperature Probe A3587 and Temperature Indicator A3586 provide local monitoring of vacuum pump inlet temperature.

P res su re Transducer A3547 provides subcooler pressure monitor signals to a vacuum indicator on the LCC LH2 monitor panel.

Subcooler Inlet Temperature Probe A3574 measures line temperature up- s t ream from Subcooler A3752. Measuring instruments associated with the probe measure the vapor pressure inside the probe and provide a temperature indication as a function of vapor pressure . Temperature Indicator A3571 per- mi ts local monitoring of line temperature and is used for calibration of Tem- perature Transducer A3572. Temperature Transducer A3572 provides subcooler inlet temperature monitor signals to a temperature indicator on the LH2 monitor panel. Temperature is measured over a range of -403 to -430 F.

Subcooler discharge Temperature Probe A3583 and Temperature Gage A3582 function together to provide local monitoring of subcooler discharge temperature over a range of -403 F to -430 F.

Temperature Probe A3580, Temperature Gage A3576, and P res su re Switch A3578 function together to monitor the t ransfer line discharge temperature. (See figure 3-2.) Temperature Gage A3576 provides local monitoring of t ransfer line temperature and is used for calibrating P r e s s u r e Switch A3578. Pressu re Switch A3578 provides t ransfer line temperature monitor signals to the LCC temperature recorder and a temperature indicator on the LCC LH2 monitor panel.

Transfer Subsystem (Figure 3-2) - LH2 t ransfer between the LH2 storage facility and the S-IV stage LH2 tank is controlled by the main fill and topping control t r ans fe r line valve complex within the umbilical tower. Major components within this valve complex are: Main fill Pneumatic Valve A3911, replenish Pneumatic Valve A3910, t ransfer line vent Pneumatic Valve A3912, and helium heat exchanger LH2 inlet Pneumatic Valve A3917. The pneumatic valves a re controlled by individual

' solenoid valves that route 750-psig .GN2 control pressure from valve panel B (volume 0

1.7

V) to the appropriate side of the pneumatic valve actuators. The solenoids a re controlled by the t ransfer sequence signals originated at LH2 control subsystem equipment in the LCC and the AGCS. Each pneumatic valve i s equipped with a position indicator switch that is electrically interlocked with an indicator on the LCC LH2 components panel to provide continuous monitoring of valve position.

a. Main fill t ransfer Pneumatic Valve A3911 - Opened during the main fill transfer operation and allows a 2000-gpm LH2 flow to the S-IV stage LH2 tank.

b. Replenish Pneumatic Valve A3910 - A three-position valve that controls LH2 transfer flow during the replenish operation. One valve position provides a 500-gpm LH2 flow and the second valve position limits LH2 flow to 20 gpm. During the replenish operation, the valve is alternately positioned to the 500- gpm and 20-gpm positions by Solenoid Valves A3923 and A3922 to maintain the S-IV stage LH2 tank between 99 and 99.25 percent full.

c. Pneumatic Valve A3917 - Directs pa r t of the LH2 supply being t ransferred to the S-IV stage to the helium heat exchanger (volume V) for use a s a coolant supply

d. Pneumatic Valve A3912 - Opened upon termination of LH2 t ransfer operations to vent GH2 from the t ransfer line to the launch facility burn pond. During LHg transfer operations, the valve remains closed.

e. Pressure Transducers A3900 and A3916 - Monitor main fill and topping control line pressure during LH2 transfer operations and provide p re s su re monitor signals to a pressure indicator on the LH2 monitor panel. The differential pressure ranges from 0 to 30 psig.

f . Relief Valve A3932 - Provides overpressure protection for the main fill and topping control lines by venting the lines to the launch a rea burn pond when line pressure reaches 9 2 (k 2) psig.

1. 3. 3 Control Subsystem - The control subsystem consists of equipment in the launch control center, the automatic ground control station, and the electrical equipment house. These three a reas and the control subsystem equipment within each a rea a r e identified in figure 1-1.

1. 3 .3 .1 Launch Control Center ( LCC) . Control subsystem equipment in the LCC consists of the panels and control equipment necessary for initiating, monitoring, and controlling LH2 transfer operations. Equipment descriptions a r e provided below:

a . Relay Distributor Assemblies - A relay distributor assembly is mounted in each of the two propellant loading racks to provide a point for power distribution from the LCC to the storage and launch areas .

1.8

b. LH2 Timer Assembly - Contains t ime relays for use in automatic sequences and power switching relays for controlling system power busses and associated components.

c. LH2 Control Panel - Provides controls fo r initiating operations and provides indicators f o r monitoring operations. The controls and indicators a r e described below.

(1) Power ON-OFF Switch - Controls electric power to other LH2 control panel components.

(2) FUNCTION SELECTOR SWITCH - A four-position switch used for selecting one of four modes of system operation: off, operate, simulate, o r manual. With the switch at the OPERATE position, the LH2 system is set for automatic operation, which requi res only the momentary depression of sequence buttons to initiate automatic sequencing of system operations. At the SIMULATE position, the switch also provides for automatic sequencing of system operations, but without LH2 transfer. This mode is used only to verify the operation of system components. When turned to the MANUAL position, the switch t ransfers individual control of system components to controls on the LH2 components panel. A t the OFF position, the switch stops all t ransfer operations.

(3 ) CONTROL RETURN Switch - Used to re turn control of t ransfer operations to S-IV stage propellant loading control equipment when required.

(4 ) Prerequis i te Indicators - The indicators a r e mounted ac ross the top of the panel. A s each prerequisite is completed, a par t icular indicator will light. When all the prerequisites a r e met , and the S-IV stage LH2 tank is ready for filling, the STANDBY indicator will light in the FILL sequence group of indicators.

(5) FILL, SECURE, and DRAIN Pushbutton Switches - Used to simulate the fill, secure, and drain sequences as required. The fill sequence may be initiated only after the fill sequence STANDBY indicator and the prerequisite indicator lamps a r e lighted. of the sequence may be monitored on indicators located to the right of the FILL push-button. monitored in a like manner.

Progress

The secure and drain sequence a r e

d. LH2 DC Power Panel - Provides dc power to propellant loading racks Ro. ci and No. 7.

e. LH2 Distributor Assembly - Provides a distribution point for electrical power ~ and control circuits.

1.9

f .

~ 1.10

g.

h.

LH2 Monitor Panel - Provides ten gages for monitoring various system conditions in the storage facility, launch a r e a , and the vehicle.

(1) Filter Differential P r e s s u r e Gage - Indicates the p re s su re drop ac ross t ransfer line Filter A3905 (figure 3-2).

(2) Transfer Line P r e s s u r e Gage - Indicates the LH2 p res su re in the transfer line.

(3 ) Transfer Line Outlet Temperature Gage - Indicates the t ransfer line temperature of LH2 leaving the storage area.

(4) Vehicle Vent P r e s s u r e Gage - Indicates the vehicle vent p re s su re in the vent stack.

(5) Subcooler Level Gage - Indicates the LH2 coolant supply level in in Subcooler A3752 (figure 3-1).

(6) Subcooler Inlet Line P r e s s u r e Gage - Indicates subcooler shell p re s su re being maintained by Vacuum Pump A3751 (figure 3-1).

(7) Subcooler Inlet Line Temperature Gage - Indicates the temperature of the LHZ entering the tube side of Subcooler A3752 (figure 3-1).

(8) Storage Tank Level Cage - Indicates the level of LH2 in Storage Tank A3753 (figure 3-1).

(9) Storage Tank P r e s s u r e Gage - Indicates the storage tank ullage pressure. The measurement range is 0 to 100 psig.

( 1 0 ) Vehicle Tank P r e s s u r e Gage - Indicates the ullage p re s su re in the S-IV stage LH2 tank.

LH2 Components Panel - Provides manual control and visual monitoring of individual component operation. Manual control of components is attained by positioning the FUNCTION SELECTOR switch on the LH2 control panel to the MANUAL position. Indicators on the panel show the condition o r position of the various components.

S-IV Stage Propellant Loading Control Panels - These panels provide controls for manual operation of system components within the umbilical tower and the S-IV s tage , and provide indicators for monitoring component operation.

1. 3.3. 2 Automatic Ground Control Station (AGCS) . the AGCS consists of ah LH2 dc power panel, an LH2 control distributor and S-IV stage propellant loading control equipment.

Control subsystem equipment in

0 Functional descriptions are given . below:

a. LH2 DC Power Panel - A rack-mounted assembly that contains indicating fuses for monitoring system power busses, and power switching relays for switching power to associated busses.

b. LH2 Control Distributor - Contains the terminal distributors, cable connections and circuit switching relays necessary to t ransfer power from the LH2 power panel to remotely located valves.

c. S-IV Stage Propellant Loading Control Eauipment - Consists of power distribution and control circuits necessary for the operation and control of system components within the umbilical tower and the S-IV stage.

1. 3. 3. 3 Electrical Equipment House ( EEH) . EEH consists of two control distributors, and LH2 dc power panel., and an LH2 monitor panel, all located in rack No. 1. E E H equipment is described below.

Control subsystem equipment in the

a. Control Distributors - Contain terminal connections and other equipment necessary to make cable connections and distribute signals to and from the LCC and storage a r e a equipment.

b. LH2 DC Power Panel - Contains indicating fuses f o r monitoring system power busses , and switching relays for switching power to associated busses.

c . LH2 Monitor Panel - Provides a means for visually monitoring liquid level and ullage p res s su re within the LH2 storage tank. The three components mounted on the panel perform the following functions:

(1) Storage Tank Level Indicator - Indicates the level of LH2 in Storage Tank A3753 (figure 3-1) .

( 2 ) Storage Tank P res su re Indicator - Indicates storage tank ullage pressure.

( 3) Fill Valve Control Switch - Used to control the position of the storage tank fill Pneumatic Valve A3302 (figure 3-1) during tank filling operations.

1 .3 .4 S-IV Stage LH2 Subsystem - Major components of the S-IV stage LH2 subsystem identified in figure 1-1 are described below.

1. 3.4. 1 LH2 Tank (Figure 3-2). tank assembly which i s comprised of the LH2 tank and a LOX tank. The LHz tank is mounted above and is physically separated from the LOX tank by a common bulkhead. During prelaunch operations, the LH2 tank is filled with approximately 28,000 gallons of LH2.

LH2 Tank E 102 is pa r t of the S-IV stage propellant

During vehicle flight, the tank supplies LH2 to the six RLlOA-3S engines 0 through individual suction lines.

1.11

Capacitance-type Mass Sensor E102, which extends from the top to the bottom of the tank, provides continuous monitoring of fuel mass . The Mass Sensor is a probe con- s i s t s of two coaxial, cylindrical elements. Each element forms one plate of a capac- tor that is in one leg of a balanced bridge network in the S-IV Stage Propellant Utiliza- tion ( P U ) system. pletion of LHz cause a proportional change in probe capacitance which unbalances the bridge network. The e r r o r signal resulting from the unbalanced condition dr ives servomotors which drive ganged potentiometers to provide feedback signals indicative of LH2 mass . These signals provide constant monitoring of LH2 mass during prelaunch fuel loading operations and vehicle flight. A s imi la r arrangement of a capacitance probe and a balanced bridge a r e used in the S-IV stage LOX system to monitor LOX m a s s (volume 11).

Variations in LH2 m a s s during prelaunch fueling and inflight de-

During prelaunch fueling operations, the LH2 mass feedback signals are used to control LH2 loading operations. they feed telemetry channels for ground monitoring of in-flight LH2 depletion, and they a r e compared with LOX mass signals to determine and regulate the proportional r a t e of LOX and LH2 consumption by the RLlOA-3S engines. ( Refer to volume IX for information concerning the RLlOA-3S engine LOX and LH2 mixture ratio. ),

During vehicle flight, the signals s e rve two functions:

1 .3 .4 .2 Fill and Dra in Valve (F igure 3-2). controls LH2 flow into the LH2 tank during prelaunch fueling operations and is opened in the event of a launch cancellation to drain LH2 from the tank. controlled by Solenoid Valves E321 and E322 in response to control signals from S-IV stage propellant loading control equipment in the 1,CC and the AGCS.

Fill and drain Pneumatic Valve E l l 3

Valve actuation is

1 .3 .4 .3 Tank Pressurization Components (Figure 3-2). Tank pressurization components include valves, orifices, and pressure switches that jointly control the admission of pressurants to the LH2 tank from ground support equipment or vehicle supplies and protect the tank from overpressurization. Functions of major components within this group a re described below.

a. Vent and relief Pneumatic Valves E114 and E115 relieve excess LH2 tank pressure and a r e pneumatically opened to vent the tank during prelaunch filling operations.

b. Solenoid Valves E209 and E210 control pneumatic pressure for opening vent and relief Pneumatic Valves E 114 and E 115.

c. Solenoid Valve E211 controls pneumatic p re s su re for closing vent, and relief Pneumatic Valves E 114 and E 115.

d. Solenoid Valve E257 is opened during S-I stage powered flight to pressur ize the 1,H tank with helium f rom the S-JV stage control pressure system (volume 2 V)

e. Electropneumatic Valves E254 and E255 a r e opened to provide stepped in- c r eases in GH2 o r helium flow into the LH2 tank to compensate for in-flight decay in LH2 tank pressure .

1.12

f. p r e s s u r e Switch E276 monitors LH2 tank pressure and controls a helium pressurization supply solenoid valve in valve panel B (volume V) to maintain LH2 tank p res su re between 35 to 38 psia during prelaunch pressurization of the tank.

g. P r e s s u r e Switch E277 monitors LH2 tank pressure during S-I stage powered flight and controls tank pressurization supply Solenoid Valves E255 and E257 to maintain tank pressure between 30 and 32 psia.

h. P r e s s u r e Switch E278 monitors tank p res su re immediately pr ior to vehicle liftoff and provides a signal to the LCC to indicate whether o r not the tank is sufficiently pressurized for liftoff. If tank pressure is below 33.5 ('t 0.5) psia the switch signals insufficient tank pressure for liftoff.

i. P r e s s u r e Switch E279 actuates and opens tank pressurization Electropneumatic Valve E254 to increase pressurant flow into the LH2 tank when tank pressure decays to 27.5 (f 0.5) psia.

j. Differential pressure Switch E 275 monitors the differential between LH2 tank and LOX tank pressures and maintains the differential below 4 ( * 1) psid by initiating a release of LH2 tank p res su re through vent and relief Pneumatic Valve E 115 and E 114.

1 .4 SYSTEM OPERATIONS

1 .4 .1 Storage - Storage operations include storage facility purge, storage tank filling, and storage tank pressurization.

0

1.4.1. 1 Storage Facility Purge. The storage facility purge is initiated pr ior to storage tank filling to prevent the formation of explosive mixtures of air and hydrogen in the storage tank and associated lines. The purge requires external sources of GN2 and GH2. The GN2 source is attached to storage facility couplings and GK2 flows into storage tank and associated lines. The storage tank is purged by repeatedly filling it with GN2 and evacuating it until the oxygen content of the tank atmosphere is less than 1.5 percent per unit volume. The GN2 purge is followed by a warm GH2 purge which expels the GN2 and provides a pure GH2 atmosphere within the tank.

1 .4 .1 .2 Storage Tank Filling. LH2 is transported to the launch complex in mobile tankers and is subsequently pumped from the tankers into the storage tank. During the filling operations, storage tank pressure is maintained a t approximately 4 psig; excess pressure is vented to atmosphere. the tank contains approximately 125,000 gallons of LH2.

The filling operation is continued until

1.4.1. 3 Storage Tank Pressurization. After the storage tank has been filled, i t i s pressurized to 4 psig with GH2 and held a t that pressure until the initiation of LH2 transfer operations. P r i o r to the initiation of the main fill operation. however, the tank p res su re is increased to, and maintained a t approximately 42 psig'. This increase in tank p res su re provides the p re s su re head necessary to transfer LH2 through the t ransfer lines and into the S-IV stage LHz tank.

0

1.13

1 . 4 . 2 Preparation For LHg Transfer

1 . 4 . 2 . 1 Preoperational System Checkout, Following the storage tank filling operations a and pr ior to the initiation of LH2 t ransfer operations, a preoperational check is made of the LH2 pneumatic control console. storage facility purge supplies, and electrical power supplies. In addition, system manual valves a r e set up for LH2 t ransfer operations.

a. Manual Valve Checkout ( Figures 3-1 and 3-2 ) . System manual valves are positioned as follows :

( 1 ) Storage tank Manual Valves A3324 and A3380 are opened.

( 2 ) Storage tank pressurization Manual Valves A3301. A3369 and A3370 a r e opened.

( 3 ) Subcooler Manual Valve A3412 is opened.

( 4 ) LH2 t ransfer line Manual Valves A3303 and A3375 are opened.

(5) Manual Valve A3372 is opened.

( 6 ) All other manual valves a r e closed.

b. Pneumatic Control Console Checkout ( Figure 3-1 ) . trol console is placed into operation and checked out as follows:,

The LH2 pneumatic con- 0

( 1 ) Manual Valves A3712, A3713, A3714, A3715, A3720 and A3771 a r e opened.

( 2 ) Manual Vent Valves A3716, A3717, A3718, A3715, A3721, A3722, A3723 and A3724 a r e c losed . .

( 3 ) Pressu re Gages A3700, A3701, A3702, and A3703 must indicate 3500, 750 , 120, and 25 psig, respectively. Downstream Pres su re Regulators A3704, A2705 and A3706 may be adjusted to provide the cor rec t indications of line p re s su re at Gages A3701, A3702, and A3703, respectively. be adjusted at the nitrogen and helium storage facility (volume IV) .

Line p res su re measured by Gage A3700 must be

( 4 ) With cor rec t p ressures indicated at the pressure gages, the operation of Pressure Switches A3725 and A3711 is verified at the LCC LH2 control panel. Pressure Switch A3725 actuates on rising p res su re of 600 ( f 20,’ psig and lights the STORAGE FACILITY 750-PSI indicator on the LH2 control panel. p ressure of 2 1 . 4 (f 0 . 5 ) psig and lights the STORAGE FACILITY 25 PSI indicator on the LH2 control panel.

Pressure Switch A3711 actuates on a rising

a

1.14.

c. GN2 Purge Supply Checkout. must be placed in a state of readiness for purging, and GN2 purge supplies to various storage facility components must be pressure-checked and analyzed for oxygen content. and oxygen content i s measured with a portable oxygen analyzer. are made as follows:

The S-IV stage and umbilical tower equipment

P res su re checks are made with a portable mmorneter, Purge checks

(1) The vehicle vent stack purge i s checked through Manual Valve A3375.

(2) The launch area transducer cabinct purge is checked through a quick- disconnect fitting located in the top of the cabinet.

( 3 ) The storage tank steady-state vent line purge is checked through Manual Valve A341G.

(4) The subcooler transducer cabinet purge is ehecltcd through a quick- disconnect coupling located in the top of lhe cabinct.

d. Electrical Power Chcckout. Electrical power must be available to LH2 system equipment in the EEH, LCC, AGCS, and the storage facility and launch facility burn ponds. indicators as follows:

Power availability is indicated by LH2 control panel

( 1 ) The AGCS & STORAGE FACILITY indicator lights when ac power is available to AGCS and storage facility components.

(2) The STORAGE FACILITY, LCC, AGCS, TOWER S-IV & VEHICLE S-IV indicators light when dc power is available to areas that cor- respond with the indicator placards.

(3) The TOWER S-IV, S-IV 750 PSI, and STORAGE FACILITY 25 PSI & STORAGE FACILITY 750 PSI indicators light when pneumatic control p re s su re i s available from the LH2 pneumatic control console. the availability of power to EEH equipment.

The availability of pneumatic control p re s su re also indicates

(4) The STORAGE & LAUNCH FACILITIES indicator lights when power is available a t the launch area and storage facility burn ponds.

1.4.2.2 S-IV Stage LHZ Tank and Transfer Line Purge. checkout, the LH countdown. A standby period is initiated to permit the Douglas Aircraft Company (DAC) to check out and purge the S-IV stage and the LH2 transfer line. During this standby period, system control is transferred from the LCC LH2 control panel to the DAC operated S-IV stage propellant loading control panels.

Following the preoperational system is conditioned and powered for performance of the prelaunch

2

0

1.15

a. Control of transfer line vent Pneumatic Valve A3308 (figure 3-1) is t ransferred to S-IV stage propellant loading control panels from the LCC LH2 control panel by setting the CONTROL RETURN switch and turning the FUNCTION SELECTOR switch to the MANUAL position. The S-IV status STANDBY light is lighted during this sequence.

b. The S-IV stage LOX tank is pressurized with helium to 29 (i 1) psia. This pressure is maintained until LH2 tank purging is complete to prevent collapse of the common bulkhead between the LOX and LH tanks.

2

c. During the standby period, LH2 tank E102 and the LH2 transfer line receive a 50-minute helium purge that is initiated by a solenoid valve in valve panel B (volume V) . (See figure 3-2.) Helium flows from valve panel B into the S-IV stage LH2 tank through Quick-Disconnect Couplings A3155 and E250. From the LH2 tank, the helium flows through fill and drain Pneumatic Valve E113, Quick- Disconnect Couplings E 100 and A3159, Electropneumatic Valve A3150, Fil ter A3905, and to Subcooler A3752 (figure 3-1) through either main fill Pneumatic Valve A3911 o r replenish Pneumatic Valve A3910. From the main fill valve or the replenish valve, the purge supply is also routed to the helium heat exchang- e r (volume V) through Pneumatic Valve A3917. The helium purge supply is vented to the storage facility burn pond through transfer line vent Pneumatic Valve A3308 (figure 3-1) and to the launch facility burn pond through the helium heat exchanger and Pneumatic Valve A3912.

d. A s the LH2 tank and t ransfer lines a r e purged, the umbilical vent line and Quick-Disconnect Couplings A2389 and E105 a r e purged with a 50-psig helium supply routed from valve panel A (volume V) through Check Valve A2388. (See figure 3-2. ) This purge supply is a l so routed through Check Valve A3166 to purge the umbilical fill line. A second 50-psig helium purge supply from valve panel A is routed through Orifices A3167 and A3168 to purge Electropneumatic. Valve A3150 and Quick-Disconnect Coupling A3159. ued through the t ransfer line cooldown operation. The umbilical fill line purge removes GH2 boiloff during the cooldown operation and provides and inert atmosphere in the fill line pr ior to the cooldown operation. The coupling purge displaces GH2 which might escape from the couplings during LH2 t ransfer .

These purges a r e contin-

e . During the standby period purge operations, the LH2 t ransfer lines a r e checked for helium content, and when they a r e found to contain 99 percent helium. system control is t ransfer red from S-IV stage propellant loading control panels to the LCC LH2 control panel. LH2 control panel goes out to signal the t ransfer of system control.

The S-IV CONTROL RETURN indicator on the

1 .4 .3 Prelaunch LH, Transfer

1.4. 3.1 Initial Setup. fer l ines, LH2 transfer operations a r e initiated a t the LCC LH2 control pme1 by setting the FUNCTION SELECTOR SWITCH to AUTO and pressing the FILL pushbutton.

Following DAC checkout and purge of the S-IV stage and t rans-

1.16

This setup initiates automatic sequencing of the prelaunch transfer operations described in paragraph l . 2 . 2 .

1 . 4 . 3 . 2 System Interlocks. Various LH2 system operations a r e interlocked such that a given operation or a given set of conditions automatically initiates or controls another operation. These interlock functions a r e numbered and described here for reference. In subsequent descriptions of t ransfer operations the interlocks are identified by the numbers assigned below.

1.

2.

3.

4.

5.

6.

7.

8 .

9.

10.

Transfer line fill Pneumatic Valve A3306 is closed unless t ransfer line output temperature is -406 F o r less .

Transfer line fill Pneumatic Valve A3306, replenish Pneumatic Valve A3910 and main fill Pneumatic Valve A3911 a r e closed unless the S-IV stage LOX tank is pressurized. A signal f rom S-IV stage propellant loading contr.01 equipment indicates LOX tank pressurization.

Transfer line fill Pneumatic Valve A3306 and t ransfer line .cooldown Pneuma- tic Valve A3307 close with the opening of t ransfer line vent Pneumatic Valve A3308.

Replenish Pneumatic Valve A3910 and Main fill Pneumatic Valve A3911 close with an S-IV stage LHZ tank overpressure indication.

Replenish Pneumatic Valve A3910 and main fill Pneumatic Valve A3911 close with an S-IV stage LH2 tank overfill indication.

Umbilical line vent Pneumatic Valve A3912 is interlocked closed by S-IV stage propellant loading control equipment with the opening of replenish Pneumatic Valve A3910, main fill Pneumatic Valve A3911, or S-IV stage fill drain Pneu- matic Valve E113.

Transfer line fill Pneumatic Valve A3306 is closed with the closing of S-IV stage vent Pneumatic Valves E114 and E115.

Transfer line helium purge Solenoid Valve A3318 o r t ransfer line high-pressure helium purge Solenoid Valve A3344 a r e closed with the opening of either subcooler LH2 inlet Flow Regulator A3309 o r helium heat exchanger LH2 inlet Pneumatic Valve A3917.

LH2 storage tank pressure less than 30 psig .causes t ransfer line helium purge Solenoid Valve A3318 or transfer line high-pressure helium purge Solenoid Valve 3344 to close.

LH2 storage tank main vent Pneumatic Valve A3304 js closed when LH2 storage tank p res su re is equal to or less than 2 psig, o r when LH2 storage tank pressurization Flow Regulator A3305 and t ransfer line fill Pneumatic Valve A3306 a r e closed.

1 .17

1.4. 3. 3 S-IV Stage LOX Tank Pressurization. When the LH2 control panel FILL pushbutton i s pressed, a command signal i s sent to S-IV stage propellant loading control equipment (figure 1-1) to initiate S-IV stage LOX tank pressurization. signal also lights the LHZ control panel PRESSURIZE LOX TANK indicator. pressurization to approximately 45 psia prevents collapse of the common bulkhead between the LOX tank and the LH2 tank a s LH2 is loaded into the LH2 tank. control panel PRESSURIZED COMPLETE indicator lights when pressurization is complete.

a The command LOX tank

The LH2

(Details of the LOX tank pressurization sequence a r e covered in volume 11. )

1.4. 3.4 LH2 Storage Tank Pressurization ( Figure 3-1). When the S-IV stage LOX tank pressurization sequence is complete, the fill sequence automatically progresses to LH2 storage tank pressurization. The sequence occurs a s follows:

a.

b.

C .

d.

e.

f .

The LH2 control panel PRESSURIZE STORAGE TANK indicator lamp lights.

Interlock functions 1 and 2 a r e in effect. (Refer to paragraph 1.4. 3.2.)

Vaporizer inlet Flow Regulator A3305 is opened by Pneumatic Controller A3544 and Solenoid Valve A3387. Valve opening is monitored by the LH2 components panel TANK PRESSURIZATION OPEK indicator. LH2 from the storage tank passes through Manual Valve A3301 and Flow Regulator A3305 to Vaporizer A3754 where i t is converted to GHz fo r storage tank p res s u r iza tion.

Relief Valve A3641 vents excess line pressure to the tank pressurization line, downstream from Vaporizer A3754, to maintain a maximum differential pressure of 20 psi across the vaporizer and pneumatic flow regulator.

Flow through Flow Regulator A3305 is reduced by Pneumatic Controller A3544 a s tank pressure r i s e s . The flow regulator is completely closed when storage tank ullage pressure reaches 42 psig. A3537 actuates and lights the LCC L H 2 control panel PRESSURIZATION COMPLETE indicatvr when storage tank pressure r i s e s to 30 psig. Si- multaneously, the PRESSURIZE STORAGE TANK indicator goes out. P re s su re Switch A3538 actuates a t an increasing ullage pressure of 55 psig to remove power from Solenoid Valve A3387. The closing of Solenoid Valve A3387 provides redundancy for Pneumatic Controller AS544 by en- suring that Flow Regulator A3305 is completely closed.

P res su re Switch

A continued ullage pressure r i se to 60 psig results in the actuation of P r e s - sure Switch A3539. A3396 which open Pneumatic Valve A3304. Excess tank pressure is vented through Pneumatic Valve A3304 and Check Valve A3365 to the s torage facility b u r n pond. Ullage pressure is maintained at approximately 42 psig fo r the duration of LH2 transfer.

The sLvitch supplies power to Solenoid Valves A3395 and

1.4.3.5 Transfer Line and S-IV Stage Cooldown (F igures 3-1 and 3-2). Thirty seconds after Flow Regulator A3305 is opened, the t r ans fe r line and S-IV stage cool- .

' down sequence is initiated automatically. The sequence occurs as follows:

a. The LH2 control panel COOLDOWN FILL LINE indicator lights.

b. Interlock functions 1, 2. 3, 4, 5, and 6 a r e in effect. (Refer to paragraph 1.4.3.2. )

c. Transfer line cooldown Pneumatic Valve A3307, subcooler inlet Flow Regula- to r A3309, and helium heat exchanger inlet Pneumatic Valve A3917 are opened. LH2 flows from Storage Tank A3753 through Manual Valve A3303, Pneumatic Valve A3307, the tube side of Subcooler A3752, and into the subcooler shell through Flow Regulator A3309. LH2 flow through the subcooler continues through the t ransfer line via Manual Valve A3379 and is admitted to the helium heat exchanger (volume V) through Pneumatic Valve A3917. The GH2 vented from the helium heat exchanger is routed to the launch facility burn pond through Check Valve A3377.

d. Five minutes after Pneumatic Valves A3307 and A3917 and Flow Regulator A3309 are opened, main fill Pneumatic Valve A3911 is opened. Replenish Pneumatic Valve A3910, S-IV stage fill and drain Pneumatic Valve E113, and S-IV stage LH2 tank vent Pneumatic Valves E114 and E115 are opened when LH2 is detected in the helium heat exchanger. and replenish valves and into S-IV stage LH2 tank E102. LH2 boiloff within the tank is vented to the launch facility burn pond through vent Pneumatic Valves E114 and E115, Quick-Disconnect Couplings E105 and A2389, and Check Valve A3376.

LH2 then flows through the main fill

e. The t ransfer line and S-IV stage cooldown continues until the LH2 tank is 15 percent filled. At this point in the sequence, S-IV stage propellant loading control equipment generates a command that opens transfer line fill Pneumatic Valve A3306 and lights the COOLDOWN COMPLETED indicator on the LH2 control panel. Simultaneously, the COOLDOWN FILL LINE indicator goes out. Transfer line fill Pneumatic Valve A3306 remains open as long as the S-IV stage LH2 tank is at least 15 percent filled.

1.4. 3.6 Main Fill (F igu res 3-1 and 3-2). The command signal that lights the LH2 control panel COOLDOWN COMPLETED indicator also initiates the main fill transfer operation. The sequence proceeds automatically as follows:

a. The LH2 control panel MAIN FILL indicator lights.

b. Interlock functions 1, 2 , 3 , 4, 6 , and 7 are in effect. ( Refer to paragraph 1 . 4 . 3 . 2 . )

1.19

C.

d.

e.

Transfer line fill Pneumatic Valve A3306 is open and transfer line cooldown Pneumatic Valve A3307 is closed. Valve positions are monitored by the pertinent OPEN and CLOSED indicators on the LH2 components panel. from Storage Tank A3753 through Manual Valve A3303, t ransfer line fill Pneu- matic Valve A3306, Subcooler A3752, Manual Valve A3379, main fill and replenish Pneumatic Valves A3911 and A3910, Fi l ter A3905. Electropneumatic Valve A3150, Quick-Disconnect Couplings A3159 and E100, and fill and drain Pneu- matic Valve E113, into S-IV stage LH2 tank E102. The filling ra te is approximately 2000 gpm.

LH2 flows

U'hen the LH2 tank is 92 percent filled, S-IV stage propellant loading control equipment initiates a s t a r t command to subcooler Vacuum Pump Motor A3939 which operates Vacuum Pump A3571. The 92'1, TANK LEVEL indicator on the LH., components panel lights and subcooler operations begin as follows:

Liquid Level Probe A3509 senses a low subcooler liquid level and supplies a high-pressure signal to pneumatic P r e s s u r e Controller A3513. The controller output p re s su re pas ses through Manual Valve A3412 and opens subcooler inlet Flow Regulator A3309 to admit LH2 to the subcooler shell from the t ransfer line. A s the LH2 level rises within the shell , Liquid Level Probe A3509 supplies a lower p re s su re signal to pneumatic Controller A3513. A continued drop in controller output over a range of 15 to 3 psig gradually reduces LH2 flow through Flow Regulator A3309, and thereby controls the amount of LH2 admitted to the subcooler shell.

Liquid Level Sensor A3511 actuates when the subcooler is overfilled and energizes Solenoid Valve A3386. The solenoid valve vents control p re s su re applied to Flow Regulator A3309, and the flow regulator closes, thereby terminating LH2 flow into the subcooler shell.

Vacuum Pump A3751 reduces the subcooler shell pressure. sulting p res su re drop lowers the coolant temperature sufficiently to supercool t r ans fe r line LH2 to approximately -426 F.

The re-

When the LH2 tank is 95 percent filled, main fill Pneumatic Valve A3911 is closed by Solenoid Valve A3906. This action is initiated by a DAC command that energizes Solenoid Valve A3906 and lights the LH components panel

2 95% TANK LEVEL indicator. Redundancy in terminating the inain fill operation is provided by a circuit that delays the DAC command for 15 seconds and closes transfer line fill Pneumatic Valve A3306 if main fill Pneumatic Valve A3911 fa i l s to close within 15 seconds after the DAC command is applied to Solenoid Valve A3906. The LH2 control panel MAIN FILL indicator goes out when main fill Pneumatic Valve A3911 is closed.

1 . 2 0

~

1.4. 3.7 Replenish (Figure 3-2) . The replenish operation is initiated automatically with the closing of main fill Pneumatic Valve A3911. The operation proceeds as follows:

a. The LH2 control panel REPLENISH indicator lights.

b. Interlock functions 1, 2 , 3, 4 , 5 , @, and 7 are in effect. 1.4.3.2.)

(Refer to paragraph

c . Replenish Pneumatic Valve A3910 and fill and drain Pneumatic Valve E113 a r e held open by signals f rom S-IV stage propellant loading control equipment. S-IV stage vent Pneumatic Valves E l l 4 and E l l 5 are held open by signals from Launch Operations Control (LOC) automatic circuitry in the AGCS.

d. LH2 flows into S-IV stage LH2 tank E102 through Manual Valve A3379,replenish Pneumatic Valve A3910, Filter A3905, Electropneumatic Valve A3150, Quick-Disconnect Couplings A3159 and El00 , and fill and drain Pneumatic Valve E113. LH2 flow through the replenish valve is maintained at approximately 500 gpm until the LH2 tank is 99.25 percent filled.

e . When the LH2 tank is 99.25 percent filled, S-IV stage propellant loading control equipment energizes Solenoid Valve A3922 and deenergizes Solenoid Valve A3923. The solenoid valve action repositions replenish Pneumatic Valve A3910 to provide a 20-gpm LH2 flow. Because the reduced replenish flowrate is l e s s than the LH2 boiloff r a t e , the tank LH2 level drops to the 99-percent-full level.

f. When S-IV stage propellant loading control senses this level drop, replenish Pneumatic Valve A3910 is repositioned to resume LH2 replenish at 500 gpm. The replenish flow is repeatedly cycled between 500 gpm and 20 gpm until final topping is initiated.

1.4. 3.8 Final Topping (Figure 3-2). LH tank final topping is initiated 10 seconds 2 after the S-I stage firing command is given at T -150 seconds. surization is initiated at T -150 seconds, and LH2 tank prepressurization is initiated at T -140 seconds. The topping operation occurs as follows:

LOX tank prepres-

a.

b.

C.

System interlock functions 1, 2 , 3, 4 , 5 , 6,and 7 a r e in effect. paragraph 1.4.3.2. )

(Refer to

LH2 tank vent Pneumatic Valves E 114 and E 115 are closed by Solenoid Valves E209 and E210 a t T -140 seconds. Position-feedback signals from the pneumatic valves initiate a 3000-psig helium prepressurization supply from valve panel B (volume V) . The prepressurization supply is admitted to the LH2 tank through Quick-Disconnect Couplings A3155 and E250 and Check Valve E251 and subsequently increases tank ullage pressure to approximately 36 psia.

Upon initiation of final topping, Solenoid Valve A3923 positions replenish Pneumatic Valve A3910 to provide a 500-gpm LH2 flow into the LH2 tank.

1.21

d. At T -135 seconds, Solenoid Valve E211 is opened to ensure that vent Pneu- matic Valves E114 and E115 are closed and a t T -130 seconds, E211 i s closed.

e. LH2 tank ( E102) i s 100 percent filled a t T -90 seconds. S-IV stage propellant loading control equipment closes replenish Pneumatic Valve A3910 and fill and drain Pneumatic Valve E 113. indicator and the LH2 components panel loof& TANK L,EVEL, indicator a r e 1 ighted.

The LH2 control panel REPLENISII COMPLETED

f. When tank pressure reaches 37.25 (i 0.75) ps ia , Pressure Switch E276 actuates and provides a signal that terminates the helium prepressurization supply from valve panel B. a tes the pressurization supply if tank p res su re should drop before vehicle 1 aun ch.

Switch deactuation a t 35.75 ( + 0.75) psia reiniti-

g. When the LH2 tank is completely filled and pressurized, transfer line vent Pneumatic Valve A3912 i s opened by Solenoid Valve A3925. fer line i s vented to the launch facility burn pond through Check Valve A3378.

LH2 in the trans-

h. The position-feedback signal from transfer l ine vent Pneumatic Valve A3912 opens a solenoid valve in valve panel A (volume V) purge supply that i s coupled into the umbilical fill line and the umbilical vent line.

to initiate a 50-psig He

i . When S-IV stage propellant loading control equipment senses that the LH2 tank is 100 percent filled, Vacuum Pump A3751 is stopped, subcooler inlet Flow Regulator A3309 is closed by Solenoid Valve A3386, and helium heat exchanger LH2 inlet Pneumatic Valve A3917 is closed by Solenoid Valve A3'331. ( See figure 3-1. ) If the subcooler inlet flow regulator and the heat exchanger LH2 inlet valve fail to close within 10 seconds after the closing command is given, t ransfer line fill Pneumatic Valve A3306 is closed to terminate LH2 flow.

j . At vehicle liftoff, swing a r m s No. 2 and No. 3 disconnect all S-IV stage connections to ground complex fill, vent, and pressurization lines, and the S-IV stage propellant loading control equipment c loses t ransfer line vent Pneumatic Valve A39 12.

1.4.4 Launch Cancellation - If a launch cancellation occurs during o r after prelaunch LH2 transfer, LH2 is drained from the S-IV stage LH2 tank and t ransferred back to the LHz storage tank. prerequisites for prelaunch LH2 transfer with one exception: S-IV stage propellant loading control equipment places the S-IV stage in a drain status. When the prerequi- s i tes have been satisfied and the S-IV stage i s ready for draining, the S-IV stage propellant loading control equipment generates a signal that lights the LH2 control panel DRAIN STANDBY indicator. LH2 control panel DRAIN pushbutton is pressed. goes out and the DRAIN SEQUENCE indicator lights.

The system prerequisites for draining are the s a m e as the

The drain sequence proceeds automatically when the The DRAIN STANDBY indicator

The sequence occurs as follows:

1.22

1 . 4 . 4 . 1 Initial Setup (Figure 3-1). A drain command from the S-IV stage propellant loading control equipment is applied to Solenoid Valves A3386 and A3931 to close subcooler LHZ inlet Flow Regulator A3309 and helium heat exchanger LH2 inlet Pneumatic Valve A3917 (figure 3 - 2 ) , respectively. If either A3309 o r A3917 does not close within 10 seconds after the command is applied, t ransfer line f i l l Pneumatic Valve A3306 is closed to prevent further LH2 flow from the storage tank.

0

1 . 4 . 4 . 2 LH2 Storage Tank Venting (Figure 3-1 ) . Before LHz can be t ransferred f rom the S-IV stage to LHZ Storage Tank A3753, storage tank p res su re must be vented. The venting operation is initiated by the drain command.

a.

b.

C.

d.

e.

f.

g.

The VENT STORAGE TANK indicator lamp on the LHz control panel is lighted.

Interlock function 6 is in effect. (Refer to paragraph 1 . 4 . 3 . 2 . )

Vaporizer inlet Flow Regulator A3305 is closed by Solenoid Valve A3387 to prevent further storage tank pressurization.

Replenish Pneumatic Valve A3910 is closed by Solenoid Valves A3923 and A3922. and main fill Pneumatic Valve A3911 is closed by Solenoid Valve A3906. figure 3-2. ) Closure of these valves prevents further draining of the S-IV stage LH2 tank. If closure is not effected within 15 seconds after the closing command is given, t ransfer line fill Pneumatic Valve A3306 is closed and fill and drain Pneumatic Valve E l l 3 is ope,ied.

(See

An S-IV stage LHz drain sequence secure signal is relayed to S-IV stage propellant loading control equipment, and an S-IV LOX tank pressurization signal is relayed to LOC control equipment.

A closed position-feedback signal from Flow Regulator A3305 opens vent Pneu- matic Valve A3304. The valve position is monitored by the appropriate indicator on the LHZ components panel. The storage tank is vented to the storage area burn pond through Pneumatic Valve A3304 and Check Valve A3365.

P r e s s u r e Switch A3535 actuates when tank pressure drops to 2 psig and lights the VENT COMPLETED indicator on the LCC LH2 control panel.

1 . 4 . 4 . 3 S-IV Stage LHZ Tank Pressurization. A s the LH2 storage tank is being vented , the S-IV stage LH2 tank is pressurized. When the storage tank p res su re drops to 8 ps ig o r l e s s , as sensed by P res su re Switch A3536 (figure 3-l) , the following sequence occurs:

a. The PRESSURIZE S-IV TANK indicator on the LH2 control panel is lighted.

b. Interlock functions 3, and 6 are in effect (Refer to paragraph 1 . 4 . 3 . 2. )

1.23

c. Vent Pneumatic Valves E l l 4 and E l l 5 are closed to prepare the LH2 tank for pressurization. the vent valves energizes a solenoid valve in-valve panel B to initiate a 1000- psig helium pressurization supply. The pressurization supply en ters the LH2 tank through Quick-Disconnect Couplings A3155 and E250 and Check Valve E251.

( See figure 3-2. ) A closed-position feedback signal from

1.4.4.4 LH2 Tank Draining (Figures 3-1 and 3-2). LH2 tank draining is initiated when tank ullage pressure increases to a minimum of 17 psig. The LH2 control panel PRESSURIZED COMPLETE indicator lights, and the drain sequence occurs as follows:

a. Interlock functions 3 and 6 are in effect. ( Refer to’paragraph 1.4.3.2. )

b. Main fill Pneumatic Valve A3911 and f i l l and drain Pneumatic Valve E113 are opened. If closed, transfer line fill Pneumatic Valve A3306 is also opened.

c. The LH2 control panel DRAIN indicator is lighted.

d. LH2 flows from the S-IV stage LH2 tank through fill and drain Pneumatic Valve E113, Quick-Disconnect Couplings El00 and A3159, Electropneumatic Valve A3150, Filter A3905, main fill Pneumatic Valve A3911, Manual Valve A3379, Subcooler A3752, transfer line f i l l Pneumatic Valve A3306, and into the storage tank through Manual Valve A3303.

e. Temperature Switch A3775 actuates when t ransfer line temperature increases to -406 F and signals the completion of draining by lighting the LH2 control panel DRAIN COMPLETED indicator.

1.4.4.5 Transfer Line Warmup (Figures 3-1 and 3-2). Transfer line warmup is initiated when the t ransfer line inlet temperature increases to -406 F. The sequence occurs as follows:

a. The LH2 control panel LINE WARM-UP indicator is lighted.

b. Interlock functions 3 and 6 a r e in effect. (Refer to paragraph 1.4.3.2. )

c. Transfer line fill Pneumatic Valve A3306 and main f i l l Pneumatic Valve A3911 are closed.

d. System control is returned to S-IV stage propellant loading control equipment when a closed-position feedback signal is received from main f i l l Pneumatic Valve A3911.

e. The LH2 tank prepressurization supply fr;m valve panel B is terminated.

f. Transfer line vent Pneumatic Valve A3308 is opened to vent the t ransfer line to the storage facility burn pond.

1.24

g. Vent Pneumatic Valve A3304 is closed by the closed-position feedback signal from t ransfer line fill Pneumatic Valve A3306, or when the storage tank ullage p res su re drops to 2 psig.

The t ransfer line is vented fo r 3 hours before line vent Pneumatic Valve A3308 is closed.

Automatic sequencing terminates a t this point in the sequence, and the LH2 control panel LINE WARM-UP indicator goes out.

h.

i.

1 . 4 . 4 . 6 Manual Inerting (F igures 3-1 and 3-2 ) . Manual inerting of the t ransfer line and LH2 storage facility is initiated a t the closure of line vent Pneumatic Valve A3308. The READY FOR INERTING indicator on the LH2 control panel is lighted and the sequence occurs as follows:

a.

b.

C.

d.

e.

1 . 4 . 5

Solenoid Valve A3318 is closed by a signal from the LH2 components panel.

Manual Valves A3301, A3303, and A3343 are closed.

Manual Valves A3336 and A3337 are opened to supply low-pressure GN2 to the t ransfer line. The GN2 supplied at Coupling A3937 passes through Manual Valve A3337, Orifice A3606, Manual Valve A3336, and Check Valve A3348 to the t ransfer line.

Helium heat exchanger LH2 inlet Pneumatic Valve A3917 is opened for 1 hour. Subcooler inlet Flow Regulator A3309 is opened for 5 minutes. The helium heat exchanger and Subcooler A3732 a r e purged by GN;! supplied to the t ransfer line.

Steady-state vent Flow Regulator A3338 is opened by Pneumatic Controller A3551 to vent Storage Tank A3753. Tank pressure may be maintained a t a positive p re s su re of approximately 0 . 5 psig by adjusting Pneumatic Controller A3551.

S-IV Stage Propulsion System Supply

1 . 4 . 5 . 1 LH2 Tank Pressurization ( Figure 3-2 ) . LH2 tank pressurization provides necessary structural integrity to the S-IV stage propellant tank assembly and provides a net positive LH2 suction head to the RLlOA-3S engine fuel pumps.

a. The S-IV stage LH2 tank E102 is pressurized to a nominal pressure of 3 6 . 5 psia during LH2 replenish operations. f rom S-IV stage propellant loading control equipment when the tank is 95 percent filled. Immediately prior to liftoff, P re s su re Switch E278 signals inade- quate tank p res su re for liftoff if tank p res su re drops to 3 3 . 5 (i 0 . 5 ) ps ia , and the launch is halted. However, if p ressure is 3 4 . 5 ( f 0 . 5 ) ps ia , the pres - sure switch signals minimum pressure for liftoif and the launch operations a r e continued.

Pressurization is initiated by commands

To maintain tank pressure between 37.25 ( * 0 . 7 5 ) psia and 35 .75

1 . 2 5

ps ia , P re s su re Switch E 276 controls the opening of pressurization solenoid valve in valve panel B.

b. LH2 tank pressure remains substantially constant during S-I stage powered flight until the LH2 p res t a r t command is initiated. An appreciable p re s su re drop occurs, however, during LH2 chilldown of the RLlOA-3S engine. Pres- su re Switch E277 opens Solenoid Valve E257 and Electropneumatic Valve E255 to admit make-up p res su re to the LH2 tank from the S-IV stage control pres- s u r e system i f pressure drops to 30.5 (f 0.5) psia. supplied through Solenoid Valve E257, Check Valve E258, Orifices E259 and E253, Electropneumatic Valve E255, and Orifice E256, increases tank p res - su re t o 31.5 ( * 0.5) psia and make-up pressurization stops. P r e s s u r e Switch E277 maintains tank pressurization between 30.5 (i 0.5) psia and 31.5 (k 0.5) psia until chilldown operations are completed. A system interlock function at approximately 4.6 seconds after separation of the S-I stage and the S-IV stage r ende r s the make-up pressurization system inoperative for the remainder of S-IV stage powered flight. Additional LH2 tank pressurization is also provided, as required, by the action of LH2 tank P r e s s u r e Switch E279. P r e s s u r e Switch E279 actuates Electropneumatic Valve E254 a t a tank ullage p res su re of 27.5 (& 0.5) psia and remains operative until the propellant utilization ( P U ) system commands Electropneumatic Valve E254 to remain open during the la t te r period of S-IV stage powered flight. The p res su re switch is rendered inoperative as long as the ullage p re s su re remains above 29.5 ( A 0.5) psia. Electro- pneumatic Valve E254 provides helium for tank pressurization until 4.6 seconds after S-I and S-IV stage separation when the make-up pressurization system is rendered inoperative.

Helium a t 3000 psig,

c. A f t e r engine ignition, LH2 tank pressurization is supplied by 340-psia GH2 from RLlOA-3S engine LH2 tank pressurization lines. The p res su re is reduced to approximately 34 psia by Orifice E253 to maintain adequate tank p res su re a s LH2 is depleted. Electropneumatic Valve E255 admits additional GH2 to the LH2 tank through Orifice E256 upon receipt of a signal from Pres- su re Switch E277 that indicates a tank p res su re drop below 30.5 (& 0.5) psia. P r e s s u r e Switch E277 controls the opening and closing of the electropneumatic valve to maintain LH2 tank p res su re a t 30.5 (i 0.5) psia until approximately 370 seconds after RLlOA-3S engine ignition.

d. Additional LH2 tank pressurization is required during the last 100 seconds of powered flight to ensure that a net positive suction head is maintained at the RLlOA-3S engine turbopump inlets. At approximately 370 seconds after engine ignition, a propellant utilization system command opens Electropneumatic Valve E254 to admit additional GH2 from the engine LH2 tank pressurization lines to the LH2 tank. GH2 a t approximately 340 psia is applied to Orifice E 252 and the flow through the orifice increases tank p res su re approximately 10 psig. For the remainder of S-IV stage powered flight LH2 tank pressurization is maintained by Electropneumatic Valve E254 and Orifices E252 and E253.

1.26

e. During flight differential Pressure Switch E275 prevents the possible collapse of the common bulkhead between the LOX and LH2 tanks due to excessive LH2 tank pressure. When LHz tank p res su re exceeds LOX tank pressure by 4 ( + 0.1) psid, Differential Pressure Switch E275 actuates and sends a signal that energizes Solenoid Valve E209. Control pressure flow through the solenoid valve opens vent Pneumatic Valve E115, to reduce LH2 tank pressure .

f. Vent Pneumatic Valves E114 and E115 provide LH2 tank overpressure protection by relieving excess pressure at 44 psia. The valves r e sea t at 41 psia.

1.4.5.2 LH2 Consumption ( Figure 3-2). engine chilldown. The fuel inlet shutoff Pneumatic Valves E l ( volume Do a r e opened during S-I and S-IV stage separation to supply LH2 to the RLlOA-3S engines. LH2 flows from the LH2 tank, through each of s ix suction lines and fuel inlet shutoff Pneumatic Valves E l .to each RLlOA-3S engine turbopump inlet. During engine operation the LH2 mass flowrate to each engine is approximately 5.88 pounds pe r second. M a s s Sensor E107 senses LH2 m a s s and provides continuous monitor signals to the S-IV stage P U system. When LH2 depletes to approximately 83 pounds of residual fuel, the S-IV stage P U system initiates engine cutoff.

LH2 consumption is initiated at RLlOA-3S

1.27

I r

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STORAGE FACILITY 1 BURN POND g TORAGETANK

* I

r 'I ,

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EXCMANCER

INLET VALVE ..............

=-F? ..............

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VALVE PA1

...................... VALVE

......... .,

i ----- -- -.- l- . ................................... -. 1 - - ............ ............ CONTROL DC POWER LOADING ................

CONTROL EQUIPMENT

MONITOR PANEL DISTRIBUTOR PANEL

: ACCS -....e i ---- :-:-:----: ----. .- . . .

... ......

.................................................. : : :

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1 ------ :-: ---- i----:-- I I I

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PANEL CONTROL PANELS ASSEMBLY

.................................................... m - . * . . . . . . . . . I " t........................ : . . . . . . . . . .

CONTROLPANEL 0 . .

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ASSEMBLY NO. 2 PA NE L ASSEMBLY NO. 1

LCC

750-PSIC GL VALVE PANEL

............................... J ...............

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NOTE:

A PARENTHETICAL ROMAN NUMERAL ADJACENT TO AN INPUT OR OUTPUT ON THIS DIAGRAM IDENTIFIES THE VOLUME IN WHICH THE SOURCE OR DESTINATION IS DISCUSSED.

-

E904

Figure 1-1. Launch Vehicle SA-10 and Launch Complex 37B LH2 Fuel System-Block Diagram

1.29

SECTION 2

INDEX OF FINDING NUMBERS

This section contains an alphameric l ist by finding number, of LH2 fuel system components that function during a prelaunch countdown, during vehicle flight, o r in the event of a launch cancellation. The finding numbers listed identify components on system schematics provided in section 3. Additional columns in the index of finding numbers provide such pertinent information as component description and function, par t number, and the supplierw name and part number. A break will occur in the alphameric sequence of finding numbers when a component o r component s e r i e s is non-functional during the countdown, functional only in the event of a malfunction, functional only during a maintenance operation, o r part of another functional system.

The le t ter prefix of a finding number identifies the component location with respect to either the launch complex o r an a r e a of the launch vehicle. The letter prefixes used in this eleven-volume s e t are listed below.

FINDING NUMBER PREFIX DESIGNATED AREA

A Launch complex

B S-I stage

E S-IV stage

G Instrument unit

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SECTION 3

MI.:ClIANICAL SCHEMATICS

This section contains mechanical schematics that show the functional arrangement of LH2 l’uel system components listcd in section 2.

For a definition of the mechanical symbols used, sce MS&’C-STD-l62A.

3 . 1

A3943 A3333

A3331 e 1

‘A3335

‘A3322

A3537,

A3605 A3340

r

r-------- I A3700

% A3341

STORAGE FACILITY L _1

I

E-A3725 A3720 0’ *3702 I’ f

+

c 3 A3705 I

43709 ip A3721

A3533

\

A3416 A3551

- A3397 CN 7

750 PSlC

I J PNEUMATIC CONTROL CONSOLE

‘A3610

/ @- A3506

A /-

A3346

/ la- A3507.

A3513,

I - r----- 7-1

11 1

3l- A3602

I

A3342

A3327

A3601

\ A3348 A3336

J

A3410

A3939

A3609’

STORAGE FACIL ITY I BURN POND J I-------

NOTE:

A PARENTHETICAL ROMAN NU- MERAL APPEARS ADJACENT TO THE FINDING NUMBER OF COMPON- ENTS SHOWN ON THIS SCHEMATIC FOR REFERENCE ONLY. THE ROMAN NUMERAL IDENTIFIES A SPECIFIC VOLUME IN WHICH THE REFERENCEOCOMPONENTAND ASSOCIATED SYSTEM HARDWARE I S DISCUSSED. TIE POINTS BETWEEN SCHEMATICS IN THIS VOLUME ARE KEY ED WITH EN- CIRCLED, MATCHED LETTERS OF THE ALPHABET. A FIGURE NUM- BER WITHIN THE CIRCLE IDEN. TlFlES THE SCHEMATIC ON WHICH THE CORRESPONDING TIC P31NT I S LOCATED.

L H 2 rRANSFER S U B S Y S T E M

E9049

Figure 3-1. Launch Complex 37B LH2 Fuel Storage Facility-Mechanical Schematic

3 .3

A3329

GN2 PURGE INLET

A3604 A3328

GN2 PURGE __c

INLET

I-------- 1 - I HEAT EXCHANGER I I L H 2 VENT TO LAUNCH FACILITY BURN POND b I

/ HELIUM HEAT I A3377

EXCHANGER A3950 ( P )A I------- -1

I L------,

+ - 750 PSlC '"

' CONTROL I PRESSURE SUPPLY . I

I I A2547 ( P )

VALVE PANEL 8_1 I CYnrra

d ' " ' 0 9

I A2372 I P )

, A3624

7 J

A3917 \ \c 4

I L

E A3578

I

c I A2389

I I

I I

I

I

GH2-d- TO LAUNCH FACILITY BURN POND

I

I

I L

I I-

-1 ----- I I

HELIUM HEAT I SUPPLY

EXCHANGER A3950 (Yl] _-----

r-

I 1 I

I L-

I 1

, A3949 r-

1000 OR

I ‘E250

/A23a1

I

S . 1 p STAGE CC L PRESSURE S , I -----

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I I r

,E251 I

t

t

se/ E209

I

NC

L H 2 TANK

I 1

I E 2 1 8 ( P ) -

I I S - I p STAGE CONTROL

PRESSURE SYSTEM n n L - - - - - - - - -

Y L- 340 PSlA GH 2 FROM

PRESSURIZATION LINES TO RLIOA-3S ENGINE L H 2 TANK

E279

E275

N E :

\ \ I 1 I A PARENTHETICAL ROMAN NU. MERAL APPEARS ADJACENTYO THE FINDING NUMBER OF COMPO- NENTS SHOWN ON THIS SCHEMATIC FOR REFERENCE ONLY. THE ROMAN NUMERAL IDENTIFIES A SPECIFIC VOLUME IN WHICH THE REFERENCEDCOMPONENTAND ASSOCIATED SYSTEM HARDWARE I S DISCUSSED. TIE POINTS BETWEEN SCHEMATICS IN THIS VOLUME ARE KEY ED WITH EN- CIRCLED, MATCHED LETTERS OF THE ALPHABET. A FIGURE NUM-

7BER WITHIN THE CIRCLE IDEN- TIFIES THE SCHEMATIC ON WHICH THE CORRESPONDING TIE POINT )I LOCATED.

RLIOA-3 E N C I N E Y E9050 I - - - - - - - - - - TO RLIOA-3S ENGINES J -------

8-2. Launch Complex 37B LH2 Transfer Subsystem and S - N Stage L H2 Subsystem-Mechanical Schematic

3 . 5 I

saturn - nasa · saturn i launch vehicle sa-10 and launch complex 37b functional system description...

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