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 Stowed Array
 Optics
 Array Lock
 Deployed Array
 Production Data
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An Apollo program Lunar Rover High Gain Antenna (HGA) /S-Band Array produced by RCA under sub-conract to Boeing Corporation (Prime Integrator for the Lunar Rover) as a component of the Lunar Communications Relay Unit (LCRU). This array design flew on all 3 Apollo "J" missions (Apollo 15, 16 and 17) and was used to facilitate bi-directional RF connectivity with Earth for uplink of TV transmissions from the lunar surface while the astronauts were
participating in Extra Vehicular Activity (EVA) onboard the Lunar Rover. The antenna, which was not gyro-stabilized and therefore could only be used while the Lunar Rover (LRV) was not in motion, required manual alignment; integrated optics where used to boresight the array towards the Earth.
The HGA was interconnected to the
LCRU (installed on the Rover) which housed the radio transceivers and acted as a portable direct relay station for voice, TV, and telemetry beween the crew and Mission Control Center (instead of via the Lunar Module communications system). The two-way
link also allowed Mission Control to remotely steer the Rover's onboard GCTA (Ground Commanded Television Assembly) television camera (provided antenna lock remain undisturbed).In addition to this parabolic High Gain S-Band Antenna, a low gain S-Band helical and VHF omni-directional antenna were interfaced to the LCRU for relay of voice and data.
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 Full Frontal View (1)
 Panel Right Front
 Panel Center Front
 Panel Left Front
 Rear View |
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 Lateral View
 Obverse View
 Fuel & Oxidizer Inlet Ports
 Propellant Valve Solenoid (Actuator)
 Bell Aerospace Label Plate
 Ascent Engine Propellant System Schematic
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An Apollo Lunar Module Ascent Engine Valve Package Assembly (VPA) produced by Bell Aerospace Corporation under NASA contract NAS9-1100 for Grumman (Prime for the LEM). This assembly regulated propellant flow into the engine injectors and combustion chamber of the engine; it had to function perfectly the first and only time it was employed or the crew would have perished on the surface of the moon.The VPA accepted hypergolic fuel (hydrazine (N2H4) mixed with unsymmetrical dimethylhydrazine (UDMH), commercially known as Aerozine 50, and oxidizer (nitrogen tetroxide - N2O4) from the Ascent stage propellant storage tanks; supplying it to the propellant feed section/engine assembly interface, the oxidizer and fuel lines lead into the valve package assembly. The individual valves that make up the valve package assembly are in a series-parallel arrangement to provide redundant propellant flow paths and shutoff capability. The valve package assembly consists of eight propellant shutoff valves and four solenoid-operated pilot valve and actuator assemblies. valve assembly consists of one fuel shutoff valve and one oxidizer shutoff valve These are ball valves that are operated by a common shaft. which is connected to its respective pilot valve and actuator assembly. Shaft seals and vented cavities prevent the propellants from coming into contact with each other. The VPA was also connected to separate vent manifold assemblies which drained the fuel and oxidizer that leaks past the valve seals, and the actuation fluid (fuel in the actuators when the pilot valves close), overboard. The eight shutoff valves open simultaneously to permit propellant flow to the engine while it is operating; they close simultaneously to terminate propellant flow at engine shutdown. The four non-latching, solenoid-operated pilot valves control the actuation fluid (fuel). This artifact was aquired from NORTON SALES INC Aerospace Surplus, North Hollywood California. 
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 Engine Interface Assembly
 Engraved Data
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Apollo Lunar Module Ascent Engine Propellant System tubing, interfaces and filters produced under subcontract to GAEC (Grumman Aircraft and Engineering Corporation)
for NASA Contract NAS9-1100. Components are as follows
1 - ORIFICE SUB ASSEMBLY, HYPERGOLIC FUEL; Operating Pressure 250 PSIG, Manufacturer STAINLESS STEEL PRODUCTS (Burbank Ca.)2 - ENGINE INTERFACE SUB ASSEMBLY, OXIDIZER; Operating Pressure 250 PSIG, Manufacturer STAINLESS STEEL PRODUCTS (Burbank Ca.) 3 - FUEL FILTER ELEMENT; Manufacturer WINTEC Corp 4 - VENT LINE ASSEMBLY; Manufacturer BELL AEROSYSTEMS 5 - IN LINE MICRO-POROUS FILTER, Helium: Operating Pressure 4000 PSIG 6 - MICRO-PORUS FILTER | ||||
 Flight Control Computer Card Cage
 Flight Control Computer I/O Connectors
 Flight Control Computer Tag Data
 Saturn I S-IV Gimbal Actuator Deflection Gage
 Saturn I S-IV Gimbal Actuator Obverse View
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SATURN I Block II Analog Flight Control Computer and affiliated second stage (S-IV) RL-10 Hydraulic Servo Actuator Assembly. The analog Flight Control Computer was manufactured under subcontract to IBM by COMMUNICATIONS ELECTRONICS CORP in 1962 for the Marshall Space Flight Center (MSFC); and was installed on all subsequent SATURN I Block II, IB and V launch vehicles, operating in conjunction with the Launch Vehicle Digital Computer (LVDC) . The flight computer, installed within the Instrument Unit (IU) controlled extension/retraction of each of 12 gimbal servo-actuators (2 per each of the 6 outboard Pratt and Whitney RL-10 rocket engines) on the S-IV (second stage) and 8 gimbal actuators (2 per each of the 4 outboard H-1 engines) on the S-I (first stage). The Flight Control Computer analyzed input resulting from several forces acting on the vehicle such as engine thrust, wind, gravity and internal vehicle flexing and bending. The signals, measured and inputed from the stable platform (ST-90 initially and subsequently upgraded to an ST-124) , rate signals from rate gyros or lead networks, angle-of-attack information from body-fixed accelerometers and other sensors, are shaped, given a weighting function, and combined with program data in several servo amplifiers. The resultant amplified outputs drive the servo actuators which gimbal the engines to provide nozzle deflective thrust vector control for the S-I and S-IV stages.
The computer housing was fabricated from sheet metal aluminum and made rigid by dip-brazing process. Computer wiring was accomplished by a harness running along the center of the chasis into which the Servo Amplifier, Filter and Control Attenuator Timer modules were installed. Individual Servo Amplifier cards are apportioned to qp, qy, q r (vehicle attitude rate function) for each engine.
****DETAILED DISCUSSION OF THE SERVO ACTUATOR ASSEMBLY WILL BE UPDATED ON THIS SITE SHORTLY****
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 Lateral View
 Cover Removed, Dielectric Exposed(Top View)
 Radiating Element Exposed
 IU Side COAX Connector Interface Panel
 Diagram Showing Antenna Location on Instrument Unit
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SATURN V Instrument Unit Directional CCS/PCM Antenna array. The basic structure was fabricated by Metal Research and Mr. Chris Argus of Calumet Fiberglass under subcontract to IBM (NASA Contract NAS 8-1400 )
and measures approximately 8 X 5 X 23 inches . The antenna cover, made of RF transparent epoxy impregnated fiberglass, has been removed in the adjacent images to reveal dielectric foam inserts,
and 5 helical elements, 4 in quadrapole arrangement for high gain UHF S-BAND (2282.5 MHZ @ 20 watts) and 1 monopole element The antenna was recovered by a NASA engineer from a Marshall
Space Flight Center dumpster after disposal. Because it is likely a test article, it lacks the final white titanium dioxide paint coating which would have been applied after installation on the launch vehicle. This transmit only high gain directional antenna was vehicle fixed on the IU and the radiation pattern was directed toward the earth by controlling the attitude of the spacecraft. It assumed responsibility for the Omnidirectional antenna pair once the launch vehicle exited their range (approximately 6700 nm above the earth's surface) and provided the Command and Communications System (CCS) downlink and Pulse Code Modulation (PCM)/Frequency Modulated (FM) telemetry signals to ground stations while also acting as a backup tracking transponder. Two antennas were installed for redundancy onboard the Saturn V Instrument Unit in the +Z / Position "I" quadrant (see location diagram to lower left).   |
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 Obverse View
 Inlet Port (Top View)
 Vent Port (Bottom View)
 Label Plate Oxygen Vent/Relief Valve
 Label Plate Hydrogen Vent/Relief Valve
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Apollo Saturn S-IVB (Third Stage) Liquid Oxygen (LOX) and Liquid Hydrogen (LH2) dual function Tank Vent and Relief Valves manufactured by Wallace O. Leonard Inc. under subcontract to Douglas Corporation (prime for the S-IVB). Produced in 1965 (LOX) and 1966 (LH2), they are functionally identical with the exception of their designed Relief and Re-Seat pressures consistant with the different LH2 and LOX parameters required to operate the S-IVB single Rocketdyne J2 engine.The LOX Vent-Relief valve was co-located with the LOX tank at the base of the S-IVB adjacent to the J-2 engine which powered the stage; the LH2 Vent-Relief valve was situated at the top/forward portion of the S-IVB LH2 tank. Each were commanded via the Pneumatic Control System (helium gas driven). The Vent-Relief valves were opened during ground fill/drain of the propellants and closed prior to pressurization. Additionally, these valves enabled venting while in flight if either of the tanks experienced overpressurization. The Vent-Relief valve output was applied to a nonpropulsive vent system (expelled gas was routed to two ducts positioned at 180 degrees on either side of the stage resulting in total thrust cancellation). When in flight, the LH2 Vent-Relief valve also fed the continuous vent system used to provide a thrust force required to position propellants at the aft end of each tank during coast. The system consisted of a vent line originating at the LH2 Vent-Relief valve, terminating at two low thrust nozzles located 180 degrees apart, and facing aft on the forward skirt. Venting was regulated by a pneumatically operated continuous propulsive vent module. The LH2 propulsive vents opened approximately 49 seconds after insertion (into circular Earth parking orbit) as well as during the pre-ignition Translunar Injection (TLI) Boost phase; and provided a sustained, low level thrust to keep the S-IVB propellant seated against the aft bulkheadsof their cryogenic storage tanks. Supplemented by the APS (Auxillary Propulsion System) ullage engines, these actions were critical to inhibiting J2 propellant line cavitation upon engine restart. | ||||
 LateralView
 Overhead View
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A uni-directional Pneumatic Control Valve used to regulate the flow of Liquid Hydrogen Propellant (LH2) onboard the Saturn V (S-IVB) third stage, manufactured by Subcontractor Clary Corporation (San Gabriel California) Dec 1966 on behalf of Douglas Aircraft Company (Prime S-IVB) for NASA contact NAS7-101 . This component was part of the pneumatic control system which provided gaseous Helium (Ghe) pressure to actuate all S-IVB stage pneumatically operated valves with the exception of those provided as components of the J-2 engine.
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 Label Plate
 Overhead View
 Obverse View
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An onboard Cold Helium Fill module used to facilitate loading of gaseous Helium (Ghe) into the onboard storage tanks; manufactured by subcontractor Fairchild Stratos (Manhattan Beach, California), March 1965 on behalf of Douglas Aircraft Company (Prime S-IVB) for NASA contract NAS7-101 . This component was part of the pneumatic control system which provided Ghe pressure to actuate all S-IVB stage pneumatically operated valves with the exception of those provided as components of the J-2 engine.
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 Overhead View showing Vent, Inlet and Outlet Ports
 Redundant Actuation Cylinder Heads
 Obverse View - Valve Outlet Ports A/B
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Apollo Saturn V Third Stage (S-IVB) Actuation Control Module affilated with the Liquid Hydrogen (LH2) propellant cryogenic storage tank Vent&Relief system; produced by CLARY CORPORATION under subcontract to DOUGLAS AIRCRAFT CORP (prime S-IVB) for NASA CONTRACT NAS 7-101.
The module, when command from an external ground signal (during fill operations) and from the Instrument Unit Flight Sequencer (during liftoff and flight) pneumatically triggered actuation of the Vent valve, off-loading excess hydrogen gas from via the non-propulsive
vent ducts on the stage. See S-IVB Vent and Vent/Relief Valves (listed elsewhere on this page) for related discussion.
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 Inlet Port
 Outlet Port
 Tag Data
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Saturn V Third Stage Directional Control Fuel Vent Valve manufactured by CALMEC Corporation for Douglas Aircraft Corporation (primary integrator for the S-IVB under
NASA Marshall Space Flight Center Contract NAS7-101). During ground fueling operations, the valve routed Gaseous Hydrogen (GH2) overboard to the burn pond via the LH2 Ground Vent Disconnect Coupling (an example of which
can be seen below in this collection). During flight, the control valve diverted GH2 though the stage non-propulsive vents for explusion into space. The valve was pneumatically operated utilizing 475 psig gaseous helium
from onboard storage tanks.
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 Valve Interior
 Valve Interior
 Label Plate
 Overhead View
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A Saturn V Third Stage (S-IVB) Fuel Tank Relief Valve utilized in conjunction with the Liquid Hydrogen (LH2) Cryogenic storage tank and propellant distribution system; manufactured by subcontractor W.O. Leonard Inc (Pasadena, California) un behalf of Douglas Aircraft Company (Prime S-IVB) for NASA contract NAS7-101. This component was part of the vent and relief system capable of relieving all excess pressure accumulated from over-pressurization or fuel boil-off during fill and flight operation.
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 Male Coupling(S-IVB Interface)
 Exhaust Port (Towards Burn Pond)
 Tag Data
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Gaseous Hydrogen Ground Vent Line Disconnect coupling manufactured by Fairchild Stratos (Western Division) for Douglas Aircraft Corporation on behalf of the NASA Marshall Spaceflight Center under contract NAS7-101 ( Saturn V S-IVB Contract ). The coupling was intefaced to the Saturn Third Stage via Launch Utility Tower (LUT) Service Arm 7 and provided for safe routing of excess Gaseous Hydrogen (GH2) exported from the stage Vent and Relief Valve to the Hydrogen burn pond.
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 Obverse View
 Inlet Port (Top View)
 Outlet Port (Bottom View)
 Label Plate(Top View)
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An Apollo Saturn V S-II (Second Stage) Hydrogen Vent valve produced by CALMEC Manufacturing Company under subcontract to North American-Rockwell Corporation (prime for the S-II). This assemblage is a component of the Venting Subsystem for the S-II (Saturn V Second Stage which employed five Rocketdyne J-2 LH2/LOX bipropellant fueled engines).
The venting subsystem is used during loading and flight operations of the Saturn V S-II. The valve was physically located atop the S-II Liquid Hydrogen (LH2) tank and provided overboard discharge of excess propellant. While the propellant tanks were being loaded, the vent valve was
opend by electrical signals from ground equipment to allow the gas created by propellant boil-off to leave the tanks. The valve is spring-loaded to be normally closed, but a relief valve would open if pressure in the tanks reached an excessive level.
The valve is capable of venting enough gas to relieve the pressure in its tank; two are provided in the LH2 propellant tank for redundancy.
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 Feedline Input (From Tank)
 Output Port (To J2)
 Valve Tag Data
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A Saturn V Second Stage (S-II) Liquid Oxygen (LOX) and Liquid Hydrogen (LH2) Pre-Valve manufactured by North American Aviation (NAA) Space and Informations Systems Division in 1968 under NASA Contract NAS 7-200 (primary contract awarded to North American Rockwell for design/build of the Saturn V Second Stage) . The Pre-Valve was a critical component of the S-II Propellant Delivery System and regulated the flow of propellants through separate feedlines to each of the Rocketdyne J2 engines.The 8 inch prevalves were normally open, pneumatically actuated, electrically controlled, butterfly-gate type valves. A built-in four-way pneumatic control solenoid permited 750 +/- 50 psig helium pressure to actuate the butterfly-gate. Should a loss of pneumatic or electrical power occur, the prevalves were designed to be spring actuated to return to the open position. During ground operations, the Pre-Valve was opened to permit propellant fueling and in conjunction with the recirculation subsystem, allow the propellant to cycle through the feed lines and valves servicing the J2 engines, maintaining uniform cryogenic density and temperature, and precluding the formation of gas in propellant plumbing. Following propellant tank loading and all the way up to the point of S-IC (Saturn V first stage) separation, the Pre-Valves were commanded to remain shut and were opened in conjunction with second stage ignition. They would normally remain open during S-II powered flight unless a signal was received from the engine shutdown system. The valves also provided a redundant shutoff of propellant concurrent with main valve closure. | ||||
 Inlet Port
 Obverse View
 Vent Port
 Tag Data
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Apollo Saturn IB S-IV (Second Stage) Gaseous Hydrogen (GH2) dual function Tank Vent and Relief Valve manufactured by CALMEC under subcontract to Douglas Corporation (prime for the S-IV NASA CONTRACT NAS7-1).
The Valve provided relief and overboard venting of excess Gaseous Hydrogen from the fuel tank which serviced the 6 RL-10 engines; routing via the
non-propulsive vent ducts into space (during flight) or the GH2 Burn Pond (during ground fueling operations).Vent valve actuation was commanded from an external ground signal during fill operations, and from the flight sequencer during liftoff and flight. The vent valve was designed to open in a maxiumum of 0.1 second upon command. The relief valve, which provided a backup capablity in case of vent valve failure, opened at 42 psia and reseated at 39 psia, and had a flow/relief capability of 2 pounds/second at sea level. | ||||
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