Sib Lox Pressurization And Vent System Diagram

Saturn Diagram

Pressure from jhe ground GN2 system to open the lox vent-and-relief valve. Flight Pressurization. During the boost phase, lox is supplied to the engine heat exchangers. Gox from each heat exchanger flows into a common manifold, through the gox flow control valve, and into lox tank O-C. The outer lox tanks receive gox through the upper interconnect lines and manifold. The gox flow control regulator controls the flow and maintains a pressure of 50 psia. Overpres-surization is prevented by the lox...

Gas Generator and Control System

The gas generator and control system controls engine start sequencing and supplies power to drive the turbopump. Solid Propellant Gas Generator. A solid propellant gas generator (SPGG) installed on the liquid propellant gas generator (LPGG) combustor of each engine, starts the engine by supplying large volumes of gas to spin the turbine. Upon receipt of the engine ignition command, two initiators installed in the SPGG ignite pellets in an igniter inside the SPGG and the pellets in turn start...

Heat Shield Details

Cross Stiffening Brackets

LAYER (0.25-INCH SQUARE HEAT REFLECTING CRES CELLS, 0.0015 FOIL jApp LAYSS HEAT SHIELD SUPPORT CHANNEL (CRES) BRAZING FOIL LAYER (0.0015 AG-CU-LI) M-31 INSULATION IMPREGNATED INTO HONEYCOMB CORE INSULATION RETAINING HONEYCOMB CORE LAYER (0.50-INCH SQUARE CRES CELLS, 0.0015 FOIL THICKNESS) LAYER (0.25-INCH SQUARE HEAT REFLECTING CRES CELLS, 0.0015 FOIL jApp LAYSS HEAT SHIELD SUPPORT CHANNEL (CRES) SPACER (0.50 DIA, 0.06 WALL CRES TUBE) SPACER (0.50 DIA, 0.06 WALL CRES TUBE) The S-IB stage...

Saturn Configurations

Skylab Technical Drawings

Apollo command & service modules lunar module & spacecraft lm adapter apollo command & service modules lunar module & spacecraft lm adapter with ullage thrust capability, and a flared aft interstage to mate with the S-II stage. The first eight booster stages (S-I) were initially designed, developed, manufactured, and tested by MSFC personnel. Responsibility for subsequent stages was transferred to Chrysler Corporation Space Division (CCSD). On August 20, 1963 CCSD was awarded a...

Abort Limits

PITCH AND YAW 5 0.5 DEG SEC LIFTOFF (T +0) TO T + 1 MIN 40 SEC T + 1 MIN 40 SEC TO S-IVB CUTOFF 10 i0.5 DEG SEC ROLL 20 0.5 DEG SEC LIFTOFF TO S-IVB CUTOFF 1. DURING S-IB POWERED FLIGHT THE TWO CUES FOR PLATFORM FAILURE REQUIRING AN IMMEDIATE SWITCHOVER ARE 2. AFTER LV RATE SWITCH DEACTIVATION THE PRIMARY CUE IS LV GUID LT - ON AUTOMATIC ABORT LIMITS (LIFTOFF UNTIL DEACTIVATION AT T + 1 MIN 40 SEC) 1. RATE PITCH-YAW 5 0.5 DEG SEC S-IB ENGINE FAILURE (SUBSEQUENT TO AUTO ABORT DEACTIVATE AT T + 1...

Sivb Propellant Tank Insulation

ACCESS DOOR ACCESS DOOR BALSA INSULATING RING' ACCESS DOOR ACCESS DOOR BALSA INSULATING RING' -AFT ENVIRONMENTAL CONTROL CHAMBER SEAL -AFT ENVIRONMENTAL CONTROL CHAMBER SEAL AFT DOME EXTERNAL INSULATION AND ENVIRONMENTAL CONTROL CHAMBER DETAILS COMMON BULKHEAD - AFT DOME JUNCTION CRYOGENIC INSULATION DETAILS 1. AREAS SHOWN BY THE FOLLOWING SHADING HAVE ABLATIVE COATING OF THE INDICATED THICKNESS. 2. AREAS SHOWN BY THE FOLLOWING SHADING ARE SPECIALLY PREPARED ENAMELED SURFACES WITH COATING OF...

Safe And Arm Device Characteristics

EXPLOSIVE INSERTS OPERATIONAL TEMP RESPONSE TIME TWO 2.5 gr PETN LEADS -65 TO +I65 F ROTOR SHAFT WILL ROTATE 90 DEG UNDER NO LOAD IN LESS THAN 50 MSEC WITH 28 + 4 Vdc APPLIED TO SOL THE S& A DEVICE HAS BEEN QUALIFIED THROUGH 8-FOOT DROP TESTS AND SHOCK TESTS OF 35 g MAGNITUDE, THREE SHOCKS IN EACH OF THREE AXES. SHOCKWAVES WERE 1 2 SINE WAVES, 8 MSEC DURATION armed. The S& A device electrical circuitry provides monitoring and actuation functions for the device, but contains no provisions...

Eds Power Switch

The EDS POWER switch (Z-17, figure 3-1) should be in the EDs power position during prelaunch and launch operations. The switch, if placed in the OFF position results in an EDS Unsafe function. This function has the following effect on the launch countdown. 1 If the switch is turned OFF before automatic sequence, the automatic sequence will not be entered. 2. If the switch is turned OFF during the automatic sequence (starting at T-187 sec), but prior to T-30.0 sec, the countdown is stopped at...

Hydraulic System Diagram

Saturn Diagram

ACCUMULATOR-RESERVOIR AND MANIFOLD CHARACTERISTICS ACCUMULATOR SECTION OF MANIFOLD WITH HIGH PRESSURE RELIEF VALVE IS NOT SHOWN pressure of 2850 psig to allow system checkout and to hold the engines in the neutral position at ignition. As each engine ignites, its main hydraulic pump, driven by the engine turbopump, begins delivering high pressure fluid. After the ignition sequence, the all engines running signal removes power from the auxiliary pump motors.

Saturn Ib Sequence Of Events

Time before liftoff (minutes) -3 00 -2 00 -1 00 aux hydraulic pumps on s-ib heaters on lox dome purge on lpgg lox injector purge on thrust chamber ftjet injector purge on t calorimeter purge on time after liftoff (minutes) 3 00 7 00 8 00 * ignition engine 6 & 8 i ignition eng 2 & 4 5holddown arms released tail masts retracted service arms retracted single engine cutoff capability time from separation command (seconds) _1 multiple engine cutoff capability a inboard engines cutoff .1 l l...

RF Assembly Telemetry Link GF

The RF assembly uses the input signal to frequency modulate a ESE DISPLAY HARDWIRE AUXILIARY DISPLAY OUTPUT SHOULD BE PREDICTED VALUE +2 FULL SCALE. OUTPUT SHOULD BE PREDICTED VALUE +1 FULL SCALE SIGNAL LEVEL SHOULD BE PREDICTED VALUE + 10 OF LEVEL SPECIFIED VHF oscillator in the FM transmitter. The 1.5-W signal is raised to 20 W nominal by a power amplifier. The high power signal is then filtered to suppress harmonics and supplied to the telemetry system RF coupler.

Emergency Detection System

An emergency detection system (EDS) network must be provided that can instantly detect vehicle failure conditions, and either initiate automatic abort or warn the crew that a manual abort is necessary. Manual abort must be initiated on at least two separate and distinct indications. In the event of conflicting information between onboard crew displays and telemetry data relayed to the ground, the onboard information shall always take precedence. Abort decisions shall be made by the flight crew...

Engine Cutoff Commands

During flight, any of three basic cutoff modes will initiate H-1 engine cutoff. Those modes are malfunction cutoff, normal 4-by-4 cutoff, and range safety command cutoff. The normal 4-by-4 cutoff is the planned engine cutoff mode, where the inboard engines shut down, followed by outboard engine shutdown 4 sec later. The malfunction mode will shut down individual engines while the range safety command will shut down all engines simultaneously to effect a zero-thrust condition. The range safety...

Sivb Propellant Tank Structure

Space Shuttle Main Propulsion Engine

JAMB WELD EXTERNAL DOUBLER (TYPICAL BOTH DOMES) JAMB WELD EXTERNAL DOUBLER (TYPICAL BOTH DOMES) JAMS WELD INTERNAL DOUBLER (TYPICAL BOTH DOMES) JAMS WELD INTERNAL DOUBLER (TYPICAL BOTH DOMES) tank structure to the aft interstage. Ullage rockets and the auxiliary propulsion system mount on the aft skirt exterior electrical equipment panels mount on the skirt interior. The aft interstage assembly is 224.5 in. in length and provides the interface between the S-IVB stage and the S-IB stage. The aft...

Engine Servicing

To prepare the engines for firing, the fuel additive blender unit FABU is serviced with extreme-pressure additive ST0140RB0013, the thrust chamber fuel jacket is serviced with RP-1 fuel, and the installation of the LPGG squibless igniters, the SPGG, the SPGG initiators, the Conax valves, and the hypergol cartridges is completed. FABU Fill. A portable unit services the FABU with 105 in.5 min of extreme-pressure additive ST0140RB0013 per engine. The extreme-pressure additive, maintained at 120 10...

Hl Engine Start And Run Operation

IGNITION COMMAND AT T-3 SEC FIRES SOLID PROPELLANT GAS GENERATOR SPGG INITIATORS. SPGG IGNITES PRODUCING GASES TO DRIVE TURBOPUMP TURBINE AND IGNITE SQUIBLESS IGNITERS. TURBINE STARTS FUEL AND LOX PUMPS. PUMPS DELIVER PROPELLANTS UNDER PRESS. TO MAIN VALVES. FUEL ENTERS FUEL ADDITIVE BLENDER UNIT FABU AND MIXES WITH EXTREME-PRESSURE ADDITIVE. MIXTURE LUBRICATES TURBOPUMP GEAR TRAIN. CONTROL PRESS. FUEL OPENS MAIN LOX VALVE MLV . LOX FLOWS INTO ENGINE COMBUSTION CHAMBER. MLV MECHANICALLY OPENS...

Telemetry System Gp

Telemetry system GP1 is a PCM DDAS link that transmits realtime checkout data before launch, and measuring program information during flight. The telemetry system consists of Model 270 multiplexers 13A440 and 13A484, remote digital submultiplexer 9A700, Model 301 PCM DDAS assembly 13A485, and RF assembly 13A486. The pulse-amplitude modulated PAM data from the Model 270 multiplexers are converted to digital words in the Model 301 assembly. The Model 301 assembly then encodes the digital words...

Sib Stage Structure

Saturn Engine Config

SPLICE PLATE 16 FUEL CROSSBEAM 2 SPLICE PLATE 16 FUEL CROSSBEAM 2 -HEAT SHIELD PANELS 40 -INBOARD ENGINE FLAME CURTAIN 4 -LOWER SHROUD PANEL ASSEMBLY CORRUGATED 8 -HEAT SHIELD PANELS 40 -INBOARD ENGINE FLAME CURTAIN 4 The 7000 series aluminum alloys used in the tail unit assembly are not recommended for welded applications because of low welding efficiencies. These alloys are used in ur.pressurized areas where the assembling is done with mechanical fasteners. The tail unit thrust structure...

Sivb Structural Assemblies

AERODYNAMIC FAIRING SEGMENT 8 NON-PRIMARY STRUCTURE AERODYNAMIC FAIRING SEGMENT 8 NON-PRIMARY STRUCTURE web area is milled to a thickness of 0.086 and 0.092 in. for the areas forward and aft of the thrust structure joint, respectively. Access to the liquid oxygen tank is through the sump jamb in the bottom of the dome. Many honeycomb composite structures are used in the vehicle, the most unique is the common bulkhead that provides both the structural and thermal separation between the LH 2 and...

Separation Systems

Physical separation of the S-IVB stage from the S-IB stage must be accomplished with retromotors located on the S-IVB aft interstage, using the short coast mode in a single plane. Successful separation shall occur even should the following conditions combine in a reasonable statistical combination a. Engine thrust decay variation b. Engine dynamic thrust vector deviations c. Retro and ullage motor static and dynamic misalignment e. Single retro and ullage motor out condition Launch vehicle...

Prplnt Switch

The PRPLNT switch is a two position toggle switch with the two positions being DUMP AUTO and RCS CMD AA-56, figure 3-1 . The switch is normally in the DUMP AUTO position prior to liftoff in order to automatically dump the CM reaction control system RCS propellants, and fire the pitch control PC motor if an abort is initiated during the first 61 seconds of the mission. The propellant dump and PC motor are inhibited by the SC sequencer at 61 sec. The switch in the RCS CMD position will inhibit...

J Engine Start

PREREQUISITES OXIDIZER TURBINE BYPASS VALVE OPEN CONNECTORS INSTALLED HELIUM CONTROL VALVE DEENERGIZED, , , . IGNITION PHASE CONTROL VALVE DEENERGtZED. STAGE TANK DISCHARGE VALVE CONTROL VALVE DEENERGIZED- AUGMENTED SPARK IGNITER SPARK SYSTEM DEENERGIZED GAS GENERATOR SPARK SYSTEM DEENERGIZED CONTROL POWER ON MAINSTAGE OK NO. t AND NO. 2 PRESSURE SWITCHES OPEN-ENGINE RUNNING- START TANK DISCHARGE -DELAY TIMER lt 1.00 SEC ASI AND GAS GENERATOR J SPARKS ON HELIUM CONTROL VALVE OPENS. HELIUM FROM...

Forward Skirt Aft Skirt And Aft Interstage

These three assemblies, similar in configuration, are cylinders constructed of 7075-T6 aluminum alloy skin, external stringers, and internal frames. Their diameter is 260 in., but their lengths vary. The forward skirt has 108 stringers while the aft skirt and aft interstage each have 112 stringers. The forward skirt assembly extends forward 122 in. from the forward skirt attaching ring of the propellant tank structure. The forward skirt provides an attachment plane for the instrument unit and...

Fuel Tank Pressurization

The fuel tanks are pressurized figure 36 with helium at 29.6 to 32.4 psia starting from approximately 2 min and 43 sec prior to launch and continuing until S-IB flight is completed. The tank pressure maintains a pressure head NPSH for starting the engine fuel pumps and provides structural support by preventing the formation of a vacuum in the tanks as fuel is depleted during flight. Pressurizing components of the S-IB stage include two high pressure storage spheres, solenoid valves, pressure...

GV Plotter

The G-V plotter assembly H-49, figure 3-1 consists of a scroll of mylar tape and a G-indicating stylus. The tape is driven from right to left by pulses which are proportional to the acceleration along the velocity vector. The stylus which scribes a coating on the back of the mylar scroll, is driven in the vertical direction in proportion to the total acceleration. The front surface of the mylar scroll is imprinted with patterns consisting of high G-rays and exit rays. The high-G-rays must be...

Lox System

The five S-IB lox tanks receive lox from the facility storage system through the fill-and-drain line storing it for consumption by the eight H-l engines during boost phase figure 4-29 . The lox system tanks consist of four outer units O-l, 0-2, 0-3, and 0-4 and a center unit O-C , with a nominal system capacity of 66,277 gal and a minimum ullage volume of 1.5 percent. Sufficient ullage pressure is provided to ensure structural integrity of the lox tanks, and to maintain a net positive suction...

Direct Switches

Two DIRECT switches W-35, figure 3-1 provide for manual control of the SM RCS engines. Switch 1 controls power to the direct solenoid switches in rotational controller 1 and switch 2 controls power to the direct solenoid switches in rotational controller 2. In the down position switch 1 receives power from MNA and switch 2 receives power from MNB. In the up position both switches receive power from both MNA and MNB. Manual control is achieved by positioning the rotational control hardover to...

Spider Beam Unit

The spider beam unit holds the propellant tank cluster together at the forward end and attaches the S-IB stage to the S-IVB aft interstage. The five lox tank units are rigidly attached to the spider beam while the fuel tank units are attached with sliding pin connections. Structurally, the spider beam consists of a hub assembly, to which eight radial beams are joined with upper and lower splice plates by mechanical fasteners. The outer ends of the radial beams are spanned by crossbeams and...

EBW Detonator

EBW detonators provide the electrical-to-ordnance interface for explosive fuse assemblies. The detonators function on the EBW principle when a high voltage, high energy pulse is applied to a small diameter, low resistance wire element, the element explodes, rapidly releasing a large amount of energy adequate to detonate CONDITIONED MEDIUM SUPPLY 750 PSIG GN2 ELECTRICAL CONDITIONED MEDIUM SUPPLY 750 PSIG GN2 ELECTRICAL THE ASSEMBLY SHOWN IS TYPICAL IN EACH QUADRANT -80 F GN2 FROM GN2 DELUGE...

Instrument Compartment

Two instrument compartments located above fuel containers F-l and F-2 require environmental conditioning during preflight operations only. A ground environmental control system see Section VII supplies the required conditioning medium through swing arm no. 1 quick-disconnect. Air is used as the conditioning medium from approximately 1 day and 8 hr prior to liftoff when electronic components are activated until 30 min prior to liquid hydrogen loading at 4 hr and 45 min prior to liftoff. GN2 then...

Lox System Components

The ball-rotor gate valve is located in the fill-and-drain line leading to the sump of lox tank 0-3. The valve is spring-loaded to the closed position and is opened by pneumatic pressure applied to the actuator assembly. The actuator is designed for an operating pressure of 750 psig, a proof pressure of 1125 psig, and a burst pressure of 1875 psig. The valve position is indicated by an electrical switch for an LCC readout. The closing and opening response time is 500...

Electrical System

The H-l engine electrical system consists of armored and unar-mored electrical harnesses that interface with engine components and stage and ESE circuitry. Harnesses that have flight as well as preflight functions are armored to prevent damage to the conductors that may compromise engine operation or cause failure of the mission. Harnesses that have preflight functions only do not have armor. Those preflight functions are heater operations FABU, turbopump bearing no. 1, and MLV actuator ,...

EBW Firing Unit

Exploding bridgewire firing units, used extensively in the Saturn IB launch vehicle, provide electrical pulses to ignite the ordnance. Redundant EBW firing units in each system ensure the desired function. The solid-state electronic EBW firing units generate a high voltage, high energy, short duration pulse to fire EBW detonators or initiators. Each firing unit consists of an input filter, a charging circuit, a storage unit, a trigger circuit, and an electronic switch. Two inputs are necessary...

Range Safety System Measurements

Ten measurements figure 1-11 of the S-IB and S-IVB range safety systems are taken during flight and telemetered to ground receiving stations where they are recorded for postflight evaluation. The four command-receiver, low-level signal-strength measurements are monitored in real time on the auxiliary pad safety panel at KSC. The two S-IVB stage receiver strength signals are flight control measurements that require real-time monitoring by Mission Control Center at Houston. Texas. The S-IB stage...