Saturn V Stage I (S-IC) Overview
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- Hugh McDowell
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1 Saturn V Stage I (S-IC) Overview
2 Objectives Become familiar with the Saturn V Stage I (S-IC) major structural components: Forward Skirt Oxidizer Tank Intertank Fuel Tank Thrust Structure Gain a general understanding of the Stage I subsystems: Fuel Oxidizer Environmental Control Electrical Instrumentation Flight g Control Control Pressure Ordinance
3 S-IC Stage Structure 138 feet/42 meters high 33 ft/10 m in diameter Five F-1 engines manufactured by Rocketdyne Total Thrust = 7,610,000 lbs/ 3,451,837 kilograms Two propellants Liquid Oxygen (LOX) Fuel spell out (RP-1)
4 S-IC Stage Structure 138 ft/42 m high 33 ft/10 m in diameter Five F-1 engines manufactured by Rocketdyne Total Thrust = 7,610,000 lbs/ 3,451,837 kilograms Two propellants Liquid Oxygen (LOX) Fuel spell out (RP-1)
5 S-IC Stage Structure 138 ft/42 m high 33 ft/10 m in diameter Five F-1 engines manufactured by Rocketdyne Total Thrust = 7,610, lbs/ 3,451,837 kilograms T ll t Two propellants Liquid Oxygen (LOX) Fuel spell out (RP-1)
6 S-IC Stage Structure 138 ft/42 m high 33 ft/10 m in diameter Five F-1 engines manufactured by Rocketdyne Total Thrust = 7,610, lbs/ 3,451,838 kilograms T ll t Two propellants Liquid Oxygen (LOX) Fuel spell out (RP-1)
7 S-IC Stage Structure 138 ft/42 m high 33 ft/10 m in diameter Five F-1 engines manufactured by Rocketdyne Total Thrust = 7,610, lbs/ 3,451,838 kilograms LOX Fuel Two propellants Liquid Oxygen (LOX or RJ-1) Fuel/Kerosene (RP-1)
8 S-IC Stage Components Forward Skirt Forward Skirt Oxidizer Tank Oxidizer tank Intertank Section Intertank Section Fuel Tank Fuel Tank Thrust Structure Thrust Structure
9 Forward Skirt Provides connecting link for First & Second Stage Accommodates: Forward umbilical plate Electrical canisters Venting of LOX tank
10 Held 331,000 gallons/1,252,971 liters of liquid oxygen Oxidizer Tank -297 o F (-183 o C) Contained ring baffles for structural stability Reduced LOX sloshing Supported Helium (He) bottles
11 Intertank Section Provided structural continuity between LOX&F Fuel ltank LOX fill & drain interface to intertank umbilical Vented the fuel Vented the fuel tank
12 Fuel Tank Held 203,000 gallons/768,438 liters of RP-1 Antislosh ring baffles on inner walls Antivortex ring baffles on lower bulkhead Five LOX ducts run from LOX tank through fuel tank
13 Thrust Structure Provided support for: Base heat shield Engine fairings & fins Propellant lines Retrorockets Environmental control ducts Lower thrust ring had four hold-down points to restrain vehicle
14 Stage I Subsystems Fuel System Oxidizer System Environmental Control System Electrical System Instrumentation System Flight Control System Control Pressure System Ordinance System Fuel Tank
15 Fuel System Consisted of fuel tank, fuel feed lines, pressurization system, fill and drain components, & fuel conditioning system Held 203,000 gallons/ 768,438 liters of kerosene Provided 1,350 gallons/5,110 liters of fuel per second 10 fuel suction lines
16 Fuel System: Fuel Fill & Drain System Filled through h six-inch i Fill & Drain Line Fill & Drain Valve provided fuel shutoff Temperature Sensors used to compute fuel density Tank level filled to 102%, then the Fuel Loading Probe indicated overload After adjustments, Fill & Drain Valve closed Vent & Relief Valve Fuel Loading Probe Temperature Sensors Fill & Drain Line Fill & Drain Valve
17 Fuel System: Fuel Feed 10 Fuel Suction Lines Two/engine Supplied fuel to F-1 engine inlets Suction Lines
18 Fuel System: Fuel Feed 10 Fuel Suction Lines Two/engine Supplied fuel to F-1 engine inlets Suction Lines Prevalves Each line had pneumatically controlled Prevalve
19 Fuel System: Fuel Conditioning Bubbled GN 2 through h feed lines to prevent fuel temperature stratification prior to Ch k V l launch Wire mesh Filter prevented discharge of contaminants Check Valve Check Valve prevented fuel from entering GN 2 lines Orifice Orifice provided proper GN 2 flow into each fuel duct Filter
20 Fuel System: Fuel Level Sensing & Engine Cutoff Fuel measured by four fuel Slosh Probes & one Liquid Level Probe Slosh Probes Liquid Level Probe
21 Fuel System: Fuel Level Sensing & Engine Cutoff Fuel measured by four fuel Slosh Probes & one Liquid Level Probe Slosh Probes In case fuel depleted d before LOX, fuel system will shut down engine Cutoff Sensor provided signal voltages to shut off fuel Cutoff Sensor initiated engine cutoff as fuel falls below two sensing points on probe Liquid Level Probe Cutoff Sensor
22 Fuel System: Fuel Pressurization System Four high h pressure He Storage Bottles in LOX Tank pressurized Fuel Tank ullage High Pressure Line used for filling Storage Bottles LOX Tank Storage Bottles Filter in He fill line prevents contaminants from entering Flight Pressurization System Dump Valve for emergencies Five Solenoid Valves in parallel to control He flow to Fuel Tank ullage Fuel Tank
23 Fuel System: Fuel Pressurization System Four high h pressure He Storage Bottles in LOX Tank pressurized Fuel Tank ullage High Pressure Line used for filling Storage Bottles LOX Tank Storage Bottles Filter in He fill line prevents contaminants from entering Flight Pressurization System Dump Valve for emergencies Five Solenoid Valves in parallel to control He flow to Fuel Tank ullage Fuel Tank High Pressure Line
24 Fuel System: Fuel Pressurization System Four high h pressure He Storage Bottles in LOX Tank pressurized Fuel Tank ullage High Pressure Line used for filling Storage Bottles LOX Tank Storage Bottles Filter in He fill line prevented contaminants from entering Flight Pressurization System Dump Valve for emergencies Five Solenoid Valves in parallel to control He flow to Fuel Tank ullage Fuel Tank High Pressure Line Filter
25 Fuel System: Fuel Pressurization System Four high h pressure He Storage Bottles in LOX Tank pressurized Fuel Tank ullage High Pressure Line used for filling Storage Bottles Filter in He fill line prevented contaminants from entering Flight Pressurization System Vent and Relief Valve LOX Tank Storage Bottles Dump Valve Dump Valve for emergencies Five Solenoid Valves in parallel to control He flow to Fuel Tank ullage Fuel Tank High Pressure Line Filter
26 Fuel System: Fuel Pressurization System Four high h pressure He Storage Bottles in LOX Tank pressurized Fuel Tank ullage High Pressure Line used for filling Storage Bottles Filter in He fill line prevented contaminants from entering Flight Pressurization System Vent and Relief Valve LOX Tank Storage Bottles Solenoid Valves Dump Valve Dump Valve for emergencies Five Solenoid Valves in parallel to control He flow to Fuel Tank ullage Fuel Tank High Pressure Line Filter
27 Fuel System: Fuel Pressurization System Cold He Duct routed He from Flow Controller to Cold He Manifold LOX Tank He is distributed to Heat Exchangers on all five F-1 engines Hot He Manifold receives He & routes to Hot He Duct He carried through He Distributor & into Fuel Tank Fuel Tank Cold Helium Duct Three Pressure Switches monitor and control Fuel Tank pressurization i Cold Helium Manifold
28 Fuel System: Fuel Pressurization System Cold He Duct routed He from Flow Controller to Cold He Manifold LOX Tank He was distributed to Heat Exchangers on all five F-1 engines Hot He Manifold receives He & routes to Hot He Duct He carried through He Distributor & into Fuel Tank Fuel Tank Cold Helium Duct Three Pressure Switches monitor and control Fuel Tank pressurization i Heat Exchangers Cold Helium Manifold
29 Fuel System: Fuel Pressurization System Cold He Duct routed He from Flow Controller to Cold He Manifold LOX Tank He was distributed to Heat Exchangers on all five F-1 engines Hot He Manifold received He & routed to Hot He Duct He carried through He Distributor & into Fuel Tank Hot Helium Duct Fuel Tank Cold Helium Duct Three Pressure Switches monitor and control Fuel Tank pressurization i Heat Exchangers Hot Helium Manifold Cold Helium Manifold
30 Fuel System: Fuel Pressurization System Cold He Duct routed He from Flow Controller to Cold He Manifold LOX Tank He was distributed to Heat Exchangers on all five F-1 engines Hot He Manifold received He & routed to Hot He Duct He carried through He Distributor & into Fuel Tank Hot Helium Duct Helium Distributor Fuel Tank Cold Helium Duct Three Pressure Switches monitor and control Fuel Tank pressurization i Heat Exchangers Hot Helium Manifold Cold Helium Manifold
31 Fuel System: Fuel Pressurization System Cold He Duct routed He from Flow Controller to Cold He Manifold LOX Tank He was distributed to Heat Exchangers on all five F-1 engines Hot He Manifold received He & routed to Hot He Duct Pressure Switches He carried through He Distributor & into Fuel Tank Hot Helium Duct Helium Distributor Fuel Tank Cold Helium Duct Three Pressure Switches monitored and controlled Fuel Tank pressurization i Heat Exchangers Hot Helium Manifold Cold Helium Manifold
32 Stage I Subsystems Fuel System Oxidizer System Environmental Control System Electrical System Instrumentation System Flight Control System Control Pressure System Ordnance System Oxidizer tank Fuel Tank
33 Oxidizer System Consisted of LOX tank, fill & drain components, LOX suction lines, pressurization subsystem Tank contained ring baffles to prevent sloshing Cruciform baffle limited swirling Ring Baffles Four LOX liquid level probes monitored LOX level in tank Cruciform Baffles
34 Oxidizer System: LOX Fill & Drain System Two six-inch Fill & Drain Lines Level probe senses tank is full Third line available to fill tank through inboard suction LOX Tank Fill & Drain Lines LOX boils to maintain temperature of -297 o F Fill and drain valves open to complete drainage of LOX tank Fuel Tank
35 Oxidizer System: LOX Fill & Drain System Two six-inch Fill & Drain Lines Level Probe Level Probe sensed full tank Third line available to fill tank through inboard suction LOX Tank Fill & Drain Lines LOX boils to maintain temperature of -297 o F Fill and drain valves open to complete drainage of LOX tank Fuel Tank
36 Oxidizer System: LOX Fill & Drain System Two six-inch Fill & Drain Lines Level Probe Level Probe sensed full tank Third line available to fill tank through Inboard Suction Line LOX Tank Fill & Drain Lines LOX boils to maintain temperature of -297 o F Fill and drain valves open to complete drainage of LOX tank Inboard Suction Line Fuel Tank
37 Oxidizer System: LOX Fill & Drain System Two six-inch Fill & Drain Lines Level Probe Level Probe sensed full tank Third line available to fill tank through Inboard Suction Line LOX Tank Fill & Drain Lines LOX boiled to maintain temperature of -297 o F (-183 o C) Fill and drain valves open to complete drainage of LOX tank Inboard Suction Line Fuel Tank
38 Oxidizer System: LOX Fill & Drain System Two six-inch Fill & Drain Lines Level Probe sensed full tank Third line available to fill tank through Inboard Suction Line LOX Tank Level Probe Fill & Drain Valves Fill & Drain Lines LOX boiled to maintain temperature of -297 o F (- 183 o C) Fill & Drain Valves opened to complete drainage of LOX Tank Inboard Suction Line Fuel Tank
39 Five 17-inch Suction Lines Suction lines pass through Fuel Tank in five LOX Tunnels Inside LOX Tunnels air acted as insulation between LOX lines & fuel lines Cutoff Sensors assured safe engine shutdown Prevalves can stop flow of LOX to engine in emergency Oxidizer System: LOX Delivery Suction Lines
40 Five 17-inch Suction Lines Suction lines passed through Fuel Tank in five LOX Tunnels Oxidizer System: LOX Delivery Suction Lines Inside LOX Tunnels air acted as insulation between LOX lines & fuel lines LOX Tunnels Cutoff Sensors assured safe engine shutdown Prevalves can stop flow of LOX to engine in emergency
41 Five 17-inch Suction Lines Suction lines passed through Fuel Tank in five LOX Tunnels Oxidizer System: LOX Delivery Suction Lines Inside LOX Tunnels, air acted as insulation between LOX lines & fuel lines LOX Tunnels Cutoff Sensors assured safe engine shutdown Prevalves can stop flow of LOX to engine in emergency
42 Five 17-inch Suction Lines Suction lines passed through Fuel Tank in five LOX Tunnels Oxidizer System: LOX Delivery Suction Lines Cutoff Sensors Inside LOX Tunnels, air acted as insulation between LOX lines & fuel lines LOX Tunnels Cutoff Sensors assured safe engine shutdown Prevalves can stop flow of LOX to engine in emergency
43 Five 17-inch Suction Lines Suction lines passed through Fuel Tank in five LOX Tunnels Oxidizer System: LOX Delivery Suction Lines Cutoff Sensors Inside LOX Tunnels, air acted as insulation between LOX lines & fuel lines Cutoff Sensors assured safe engine shutdown LOX Tunnels Prevalve Prevalves can stop flow of LOX to engine in emergency
44 Oxidizer System: LOX Conditioning LOX cannot exceed -297 o F (-183 o C) or it will result in gaseous oxygen (GOX) Suction Lines Emergency bubbling corrected GOX situation Bubbling technique sent He into five Suction Lines to cool LOX Filter Valves & Orifices controlled flow of He into Suction Lines Orifices Valves Filter
45 Pressurization occurred at T-45 seconds Oxidizer System: LOX Pressurization He is supplied by GSE through He ground connection He proceeds up GOX line into LOX tank through h GOX distributor Pressure duct monitors flow of He
46 Pressurization occurred at T-45 seconds Oxidizer System: LOX Pressurization He was supplied by GSE through He Ground Connection He proceeds up GOX line into LOX tank through GOX distributor Pressure duct monitors flow of He Helium Ground Connection
47 Oxidizer System: LOX Pressurization Pressurization occurred at T-45 seconds GOX Distributor He was supplied by GSE through He Ground Connection He proceeded d up GOX line into LOX tank through GOX Distributor Pressure duct monitors flow of He Helium Ground Connection
48 Oxidizer System: LOX Pressurization Pressurization occurred at T-45 seconds GOX Distributor He was supplied by GSE through He Ground Connection Pressure Duct He proceeded d up GOX line into LOX tank through GOX Distributor Pressure Duct monitored flow of fhe Helium Ground Connection
49 Oxidizer System: LOX Pressurization GOX was added to LOX Tank for pressurization during flight GOX Distributor Portion of LOX is diverted into heat exchangers where it is transformed into GOX GOX flows from heat exchanger to GOX manifold through flow control valve, up GOX line, and into LOX tank through the GOX distributor
50 Oxidizer System: LOX Pressurization GOX was added to LOX Tank for pressurization during flight GOX Distributor Portion of LOX was diverted into Heat Exchangers where it was transformed into GOX GOX flows from heat exchanger to GOX manifold through flow control valve, up GOX line, and into LOX tank through the GOX distributor Heat Exchanger
51 Oxidizer System: LOX Pressurization GOX was added to LOX Tank for pressurization during flight GOX Distributor Portion of LOX was diverted into Heat Exchangers where it was transformed into GOX GOX flowed from Heat Exchanger to GOX Manifold through Flow Control Valve, up GOX Line, & into LOX Tank through the GOX Distributor Flow Control Valve Heat Exchanger GOX Manifold
52 Stage I Subsystems Fuel System Oxidizer System Environmental Control System Electrical System Instrumentation System Flight Control System Control Pressure System Ordnance System Forward Skirt Thrust Structure
53 Forced conditioned air into the Forward Skirt & Thrust Structure 20 minutes before cryogenic loading, flow switched from conditioned air to gaseous nitrogen (GN 2 ) Environmental Control System (ECS) Instrumentation Canisters Forward Skirt Distribution Manifold LOX Tank Orifices GN 2 flow terminated at umbilical disconnect (liftoff) Interstage Distribution Manifolds Distributed air & GN 2 to Instrumentation Canisters in Forward Skirt Vented air and GN 2 through Orifices into Thrust Structure Fuel Tank Distribution Manifold Orifices Thrust Structure
54 Stage I Subsystems Fuel System Oxidizer System Environmental Control System Electrical System Instrumentation System Flight Control System Control Pressure System Ordnance System Forward Skirt Thrust Structure
55 Two independent 28-volt DC power systems located in the Forward Skirt Battery # 1 Operational power system battery Supplied power to valve controls, venting systems, pressurization systems, sequencing & flight control Controlled solenoids Battery # 2 Measurement power system battery Supplied power to telemetry systems, transducers, multiplexers, & transmitters Electrical System Batteries Forward Skirt LOX Tank Interstage t Fuel Tank Thrust Structure
56 Main Power Distributor housed relays, power transfer switch, & other electrical equipment Forward Skirt Electrical System Switch Selector Main Power Distributor LOX Tank Relays controlled timeprogrammed circuits Sequence & Control Distributor Accepted command signals from Switch Selector Commanded staging functions Interstage Fuel Tank To Circuit Relays Sequence & Control Distributor Thrust Structure
57 Electrical System Propulsion Distributor ib t contained monitor & control circuits for propulsion system Forward Skirt Thrust OK Distributor contained circuits that shut down engines when thrust was inadequate Timer Distributor contained circuits to delay operation of relay valves LOX Tank Measuring Power Distributor Interstage Contained electrical buses Routed data from measuring racks Served as measurement signal junction Fuel Tank box To Circuit Switched data between hardwire & Relays telemetry To Distributors Thrust Structure
58 Stage I Subsystems Fuel System Oxidizer System Environmental Control System Electrical System Instrumentation System Flight Control System Control Pressure System Ordnance System Forward Skirt Thrust Structure
59 Instrumentation System Reported information on stage systems & components Provided d data on internal & external environments Monitored approximately 900 Stage I (SI-C) measurements Measurements were telemetered by Coaxial cable to GSE preflight Radio Frequency (RF) transmission to ground stations during Radio Frequency (RF) transmission to ground stations during flight
60 Instrumentation System: Measurement Used transducers, signal conditioners, measuring rack assemblies, measuring distributors, ib t & the onboard portion of the remote automatic calibration system Measured acceleration, acoustics, current, flow, flight angles, valve position, pressure, RPM s s, stress, temperature, vibration, & separation
61 Instrumentation System: Telemetry Method to remotely monitor flight data through RF links Six RF links F1, F2, F3, S1, S2, & P1 RF Assemblies & Tape Recorder located in Forward Skirt Remaining components located in Thrust Structure Forward Skirt Antennas Transmitters Tape Recorder RF Components LOX Tank Interstage Fuel Tank Measuring Racks Signal Conditioners Thrust Structure
62 Links F1, F2, & F3 Instrumentation System: Telemetry Transmitted narrow-band, frequency-type data such as strain gages, g temperature gages, g & pressure gagesg Could handle 234 measurements on time-sharing basis & 14 measurements transmitted continuously Links S1 & S2 Transmitted wide-band, frequency-type data generated by vibration sensors Each provided 15 continuous channels or max of 75 multiplexed channels Telemeter P1 Transmitted either pulse code-modulated or digital type data
63 Offset Doppler Tracking (ODOP) System Measured rate of motion the vehicle was moving away from/toward a Tracking/Receiving Station Forward Skirt Receiver Transponder Transmitter Signal was received by transponder, modified, and retransmitted back to ground Retransmitted signals were received by three Receiving Stations Separate antennas on stage were used for receiving and retransmitting the signals Transmitting Station Receiving Receiving Receiving Station # 1 Station # 2 Station # 3 Central Recording Station
64 Instrumentation System: Separation System Redundant ignition system activated separation of First Stage from Second Stage Command signal for arming & firing initiation systems were generated by Instrumentation Unit (IU) computer The IU is located above the Third Stage (S-IVB) and below the Apollo Spacecraft (CSM/LM) After LOX depletion, the IU signaled the Switch Selector and Sequence & Control Distributor to activate the exploding bridgewire firing units (explosive devices) to initiate the staging sequence
65 Visual Instrumentation: Film Cameras Four film cameras, each in a recoverable capsule Pulse Camera Two LOX tank-viewing Pulse Cameras, provided d motion pictures to show: Behavior of LOX Possible wave or slosh motions Cascading or waterfall effects of liquid id from internal tank structure Strobe Lights Stage Separation Cameras Two Strobe Lights illuminated interior of LOX tank for Pulse Cameras Two direct-viewing Stage Separation Cameras The nine ft (3 m) Fiber Optics, the coupling lens, and the objective lens connected the remotely located camera capsules and flash head Stage Separation Cameras Fiber Optics Pulse Camera
66 Visual Instrumentation: Television System Airborne Television System provided in-flight, real-time visual performance information on all five First Stage F1 engines Also stored televised pictures from fueling through First Stage separation System utilized two split fiber optic viewing systems & two cameras Fiber optic bundles transmitted images to the cameras located in Thrust Structure
67 Stage I Subsystems Fuel System Oxidizer System Environmental Control System Electrical System Instrumentation System Flight Control System Control Pressure System Ordnance System Thrust Structure
68 Flight Control System: Fluid Power System Used RP-1 and RJ-1 as hydraulic fluid Same type of fuel used for stage fuel system Ground supply of RJ-1 routed to all five F1 engines 4-Way Control Valve Feedline After ignition, RP-1 routed from High Pressure Fuel Duct to Servoactuators Return Line Center Engine directed hydraulic fluid through Feedline & 4-way Hydraulic Control Valve to supply pressure to closing ports of Gas Generator, Main Fuel Valves, & Main LOX Valves The four outboard engines directed RJ-1 through Servoactuators to ground Checkout Valve where it was returned through coupling to ground supply Filter Manifold Checkout Valve Hi h P High Pressure Fuel Duct Servoactuator
69 Flight Control System: Hydraulic Servoactuator Power control unit for converting electrical command signals & hydraulic power into mechanical outputs to gimbal engines The engine gimbaling was a closed loop system IU received inputs from its guidance system and sent signals to Servoactuators to gimbal the engines Potentiometer sensed Servoactuator position and transmitted that feedback (engine piston position) to the IU IU modified effect of control signal to continue to gimbal the engines in the required direction Potentiometer Servovalve
70 Stage I Subsystems Fuel System Oxidizer System Environmental Control System Electrical System Instrumentation System Flight Control System Control Pressure System Ordnance System
71 Supplied pressurized GN 2 to pneumatically actuate propellant system valves & purge the F-1 engines Control Pressure System To Vent and Relief Valves Onboard Control Pressure System contained high pressure nitrogen storage bottle, an umbilical coupling & tubing assembly for filling bottle, manifold assembly, & control valves at terminal ends of nitrogen distribution lines To Fill, Dump, Vent and Relief Valves Ground Control Pressure System provided direct ground pressure supply for First Stage pneumatically-actuated valves that were involved with propellant fill/drain & emergency engine shutdown system operations Onboard Purge Pressure System expelled propellant leakage Control Pressure Storage Purge Pressure Storage To Purge Systems Ground Supply To Prevalves Shutoff Valves
72 Stage I Subsystems Fuel System Oxidizer System Environmental Control System Electrical System Instrumentation System Flight Control System Control Pressure System Ordnance System
73 Ordnance System: Propellant Dispersion System (PDS) Terminated flight of Saturn V if it strayed from flight path or if it became a safety hazard PDS was a dual channel, parallel redundant system composed of two segments Radio frequency segment received, decoded, & controlled propellant dispersion commands Od Ordnance train segment consisted of ftwo exploding bridgewire (EBW) firing units, two EBW detonators, one safety & arming (S&A) device, six confined detonating ti fuse (CDF) assemblies, two CDF tees, two CDF/flexible linear shaped charge (FLSC) connectors, & two FLSC assemblies
74 For detailed view, select presentation under References below Ordnance System: PDS
75 Ordnance System: Safety and Arming Device (S&A) Remotely controlled electro-mechanical ordnance device Used to make safe & to arm S-IC, S-II, and S-IVB stage PDS s Completed & interrupted t explosive train by remote control Provided position indications to remote monitoring equipment
76 Ordnance System: Retrorockets The eight retrorockets provided separation thrust after Stage S-IC burnout Propelled Stage S-IC away from the rest of the launch stack as it progressed through to Stage II For detailed view, select presentation under References below
77 Saturn V Stage I Summary Become familiar with the Saturn V Stage I (S-IC) major structural components: Forward Skirt Oxidizer Tank Intertank Fuel Tank Thrust Structure Gain a general understanding of the Stage I subsystems: Fuel Oxidizer Environmental Control Electrical Instrumentation Flight g Control Control Pressure Ordinance
78 For More Information Apollo Mission Familiarization for Constellation Personnel Apollo-Saturn Wiki References Saturn V News Reference, August 1967 Saturn V Flight Manual, SA 503, 1 November 1968 Technical Information Summary Apollo-10 (AS-505), 1 May 1969
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