Apollo Artifacts

Gene Cernan's Apollo 17 lunar surface flown APK

This beta cloth Astronaut Preference Kit belonged to Apollo 17 Commander Gene Cernan "the last man on the moon" and was flown to the lunar surface. The APK was carried to lunar orbit in December 1972 aboard the Command Module America and was then transferred to the Lunar Module Challenger for the descent to the moon.

This bag remained on the moon inside the LM for more than three days, the longest stay of any lunar mission. After docking with the command module in lunar orbit after lunar surface operations, the APK was transferred back into America for the return trip to Earth. In total, this APK spent more than twelve and a half days in space, and a record of more than six days in lunar orbit or on the surface. It traveled a remarkable 1.3 million miles during the mission.

The Apollo 17 lunar landing site was the Taurus-Littrow highlands and valley area. This site was picked as a location where rocks both older and younger than those previously returned from other Apollo missions. Apollo 17 was the final in a series of three J-type missions planned for the Apollo program. These J-type missions can be distinguished from previous G and H-series missions by extended hardware capability, larger scientific payload capacity and by the use of the battery powered Lunar Roving Vehicle (LRV).

APKs were permitted by NASA to contain items for the astronauts' personal use, or for use by them as personal gifts. APKs carried on board the Lunar Module were limited to just one half pound per astronaut.

The APK, marked "SEC 12100087-301 S/N 1007 ASTRONAUT KIT," appears in the Apollo Storage List for mission J-3, CM 114, LM-12 dated 12-12-72. The bag is approximately 4" x 8" x 1.5" with a drawstring top and original red wax seal. It has been cut open around the back near the top.

Also included in the collection is the original NASA Astronaut Preference Kit Release Form for this APK. The form (click the photo to see a larger image), signed by Gene Cernan and Tom Stafford, acknowledges receipt of the Astronaut Preference Kit from Command Module 114. Dated December 21, 1972 (two days after the return of Apollo 17), this official form shows all of the steps necessary for the transfer of the APK from NASA to Captain Cernan after the flight. At the time, Tom Stafford was Deputy Director of Flight Crew Operations at the NASA Manned Spaceflight Center and was responsible for assisting the director in planning and implementation of programs for the astronaut group.

Apollo 17 was the first mission to be under scrutiny after the discovery of a stash of unauthorized postal covers that were flown on Apollo 15 and subsequently sold. Apollo 16 had already flown by the time of the Apollo 15 discovery. The Astronaut Preference Kit Policy permitted Apollo flight crew to carry certain items of a personal nature on each manned spacecraft flight and the items must have been carried in an approved Astronaut Preference Kit. The articles carried in the APK are for the astronauts' personal use, or for use by them as personal gifts.

When I asked him, Captain Cernan said that he didn't recall why he cut the bag open in the back. However he thought that he wanted to preserve the red wax seal. 

He told me that he recalled carrying his wedding ring, his mother’s rosary, and some photos of his family in the APK. He said that in total there were only about a dozen items flown to the lunar surface in his APK.

Apollo Lunar Module support truss

This is a support truss from the lunar module.

It is amazingly light. It must be close to (or even less than) one pound, but I don't have a scale that is that small. Comparing my body weight with and without the truss is negligible.

The truss is 21 inches long and 1 3/8 inches diameter. There is a very bold and clear stamp in red ink on both sides with part # LDW280-18847-19 A3.

Each end fitting is attached with 12 pieces of tiny hardware which are each sealed with a sealer. Curiously, it seems that each of the (24 total) hardware items are each individually stamped with a red inspector stamp (#621) and each of the main truss part number stamps is folowed by another inspector stamp #1459. The truss ends that are into the tubing are also cleanly sealed with some type of composite sealer.

Apollo Lunar Module MESA locking and deployment mechanism

This fascinating artifact is a locking and deployment mechanism for the Modular Equipment Storage Assembly (MESA) located in quad 4 of the Lunar Module decent stage. The MESA lowered like a drawbridge once the astronauts activated this mechanism upon exiting the LM.

In the G-Series mission (Apollo 11) and H-Series missions (Apollos 12, 13, & 14) the MESA was packed with equipment needed to explore and study the lunar surface (cameras, film magazines, geology equipment, sample return containers, and tools).  Later on the J-Series missions (Apollos 15-17) it also carried some parts of the Lunar Roving Vehicle, as well as spare supplies for extended lunar stay time by the LM crew (LiOH cans, PLSS batteries, etc.).

The MESA was deployed via the astronaut pulling the MESA deployment actuating handle "D handle" located on the egress platform "porch" of the lunar module.  As the cable pulled the cam, it disengaged a lock pin from a pivot arm. A "key" prevented the lock pin from interfering with its on disengagement from a locking post on the MESA as it slid into a slot.  Once this was done, lunar gravity took over and deployed the MESA downward into position. Once deployed, the MESA served as a work station for the astronauts.   

I acquired this artifact from someone who was affiliated with Grumman (manufacturer of the Lunar Module).  It is approx 10 inches long and 6 inches wide, made (almost) from one solid piece (titanium?) with an amazing assortment of angles and undercuts, a channel for the sliding part, and "ear" extensions that are almost paper thin.

The markings are a bit difficult to read but appear to be:
LDW 280M17816  ZOA6  MRR106498  LOT 3

Apollo Saturn S-IVB (third stage) liquid hydrogen vent and relief valve

This Apollo Saturn S-IVB (third stage) Liquid Hydrogen (LH2) dual function tank Vent and Relief Valve was manufactured by Wallace O. Leonard Inc. under subcontract to Douglas Corporation (prime for the S-IVB). The valve was produced in 1966.

The LH2 Vent-Relief valve, used as part of the single Rocketdyne J-2 engine system which powered the stage, was situated at the top/forward portion of the S-IVB LH2 tank. It was commanded via the Pneumatic Control System (helium gas driven). The Vent-Relief valve opened during ground fill/drain of the propellants and closed prior to pressurization. Additionally, the valve 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 bulkheads of 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.

The valve is 21" tall and 12.5" in diameter at the widest point. It weighs 45 pounds.

Thanks to Scott Schneeweis for the technical description of this artifact.

Rope memory module for the Model 100 Apollo Guidance and Navigation Computer

This is a rare rope memory module made for the Block I (before the Apollo 1 fire) Model 100 Apollo Guidance and Navigation Computer.  The computers that formed the basis of the Apollo Guidance and Navigation System (AGNS) were at the cutting edge of technology in the 1960s. They were the first to use the integrated circuit technology that subsequently gave us desktop computers and so many of the consumer electronic products that fill our lives today.

Each computer had two types of memory, erasable and fixed. The fixed memory contained the programs, constants and landmark coordinates using 36,864 terms or words, each of 15 bits length. That came to a grand total of 74 kilobytes of memory.

The fixed memory was made from coincident-current ferrite cores woven into a rope with copper wires and sealed in plastic. Software components were encoded into a core according to the "pattern" of its weave. Each core functioned as a small transformer, with up to 64 wires connected to each core. If a wire passed through a particular core, a "1" would be read. If a particular wire bypassed the core, a "0" would be read. If you wanted to change the software contained in fixed memory, you had to rewire the sealed core to change the bits. The erasable memory was made from similar materials but with a different design. Each core in the erasable memory could be changed using magnets. Turning clockwise to indicate a "1" or anti-clockwise indicating a "0".

The module is labeled: C P ASSY 1031103 NO.  1003733-011, MFG BY RAYTHEON CO., SERIAL NO. RAY 4

Thanks to Jim Loocke for the technical description of this artifact.

Brass Flashlight Designed for NASA Apollo Missions

This flashlight was made by ACR for NASA. ACR contracted out the flashlights to Fulton Industries in Wauseon Ohio. It is stamped ACR FA- 5 Serial No. 3016 Date of Mfg. 8-72. This flashlight has no known history of being on an Apollo mission. It still works brilliantly.

Launch Mission Rules for Apollo 11

This is rare original NASA manual contains the full mission rules for Apollo 11 (SA-506/CSM-107/LM-5). It is marked FOR NASA/DOD INTERNAL USE ONLY (INCLUDING APPROPRIATE CONTRACTORS). This copy was issued to Grumman (manufacturer of the LEM) and has a Grumman cover.

It is really fun to page through this is a massive 4 lb, 2 inch thick volume. Each page is dated as of update status and almost all are dated either June 2, 1969; June 20, 1969; or June 26, 1969. In addition to the very complete and specific itemized Mission Launch Rules, it details communication, aborts, redlines, crew equip and most systems and operations; extensive CSM 107 and  LM-5 sections; charts & ids of  individual switches, tanks, electrical items, and operation, environmental control, propulsion, crew duties, and activities and operational procedures.

Apollo 9 heat shield plug Lucite display

This is a circular chunk of the heat shield from Apollo 9. Heat shields were manufactured by AVCO Corporation, with integration by NAA (North American Aviation), and are comprised of an extremely lightweight fiberglass honeycomb which is hand filled by air gun with the ablative resin material. The ablative system dissipates heat as the material melts and chars during re-entry, mitigating the 20,000 degree heat experienced by the CSM as it transits through the extreme thermo-dynamic phase of the re-entry corridor.

LRL Moon Rock Secondary Sample Containers

The secondary sample storage container, used in the Lunar Receiving Laboratory allowed for easy division of samples within vacuum cabinets and had high, large threads to hold a vacuum seal in case of emergency.

Contractor press kits relating to the Apollo 11 mission

 

I've worked in marketing and PR my entire career and am fascinated by the press kits put out by NASA and by the contractors. I was fortunate to have acquired a set of complete press kits used by a journalist while covering the Apollo 11 mission. Included are press kits from IBM (Computer systems), North American Rockwell (Command Module), Grumman (Lunar Module), TRW (Engines), and several other kits not pictured here.

Lunar sample 1" scale cube

This is an exact replica 1" scale cube to those that are used to show size and orientation of lunar samples at the Lunar Receiving Lab. These scale cubes are made of machined, anodized aluminum, with engraved markings filled with baked enamel.

Kennedy Space Center access badges for the Apollo 16 mission

A collection of twelve badges that were previously owned by a 34-year KSC security guard. These badges were used as prototypes and for identification purposes. Several are astronaut badges.

Apollo spacecraft accessories bag

Bags of this type were used by astronauts to store items in the Command Module and Lunar Module. While  bags of this type flew on most Apollo missions, unfortunately the Apollo Stowage Lists did not record the serial numbers of the bags that flew to the moon.

This accessories bag was manufactured by Welson & Co. on February 5, 1971. It is part number SEB 13100114-701, serial number 1257

TR-201 Bipropellant Rocket Engine Thrust Chamber used in the Lunar Module Descent Stage

This thrust chamber was initially developed for the Apollo Lunar Module decent stage and made 10 flights during the Apollo program. This is the engine that powered the crippled Apollo 13 spacecraft from the moon back to earth because the Service Propulsion System was never used subsequent to the cryotank stir/explosion. Because the extent of damage to the SPS was unknown, there was great concern at the time that collateral damage could have caused a catastrophic malfunction (if the engine was fired). Instead the LMDE was used for the return burn and subsequent course correction. Quite a famous engine.

Flown engines, of course, are either left on the surface of the moon (Apollo 11, 12, 14, 15, 16, 17), crashed into the moon (Apollo 10), or burned up in earth’s atmosphere (Apollo 5, 9, 13).

The combustion chamber consists of an ablative-lined titanium alloy case to the 16:1 area ratio. Fabrication of the 6A1-4V alloy titanium case was accomplished by machining the chamber portion and the exit cone portion from forgings and welding them into one unit at the throat centerline. The ablative liner is fabricated in two segments and installed from either end. The shape of the nozzle extension (not installed on the example in this collection) is such that the ablative liner is retained in the exit cone during transportation, launch and boost. During engine firing, thrust loads force the exit cone liner against the case. The titanium head end assembly which contains the Pintle Injector and propellant valve subcomponents is attached with thirty-six A-286 steel ¼ inch bolts.

In order to keep the maximum operating temperatures of the titanium case in the vicinity of 800 degrees (F), the ablative liner was designed as a composite material providing the maximum heat sink and minimum weight. The selected configuration consisted of a high density, erosion-resistant silica cloth/phenolic material surrounded by a lightweight needle-felted silica mat/phenolic insulation.

The Pintle Injector, unique to TRW designed liquid propulsion systems, provides improved reliability and less costly method of fuel oxidizer impingement in the thrust chamber then conventional coaxial distributed-element injectors typically used on liquid biproellant rocket engines.

Dry mass: 300 pounds (with Columbian Nozzle Extension Installed)
Length: 51 inches - Gimbal attachment to nozzle tip (minus nozzle extension)
Maximum diameter: 34 inches (minus nozzle extension)
Mounting: gimbal attachment above injector
Engine cycle: pressure fed (15.5 atm reservoir)
Oxidizer: 50/50 N_2O_4/UDMH at 8.92 kg/s
Fuel: monomethyl hydrazine at 5.62 kg/s
O/F ratio: 1.60
Thrust: 42.923 kN vac
Specific impulse: 303 s vacuum
Expansion ratio: 16:1, 43:1 (with Expansion Nozzle)
Cooling method: quartz phenolic chamber ablation and columbium (niobium) nozzle radiation
Chamber pressure: 7.1 atm
Ignition: hypergolic, started by 28 V electrical signal to on/off solenoid valves
Burn time: 500 s for total of 5 starts; 10 350 s single burn

Thanks to Scott Schneeweis for the technical description of this artifact.

Weekend with Apollo astronauts and a shuttle launch at Kennedy Space Center

This past weekend I attended the Sims & Hankow event at the Kennedy Space Center and also had a chance to see the launch of STS-117 (Space Shuttle Atlantis). What a cool weekend to meet and chat with Apollo astronauts, mission control specialists, and others from the original American space programs.

I saw the launch (7:38PM) from the causeway. This photo is with a cheap digital camera with very little zoom applied. It is basically how I saw the launch.

About an hour later, the contrails mixing with the sunset created a terrific image behind the KSC rocket garden. I’ve never seen anything quite like those white swirling contrails against a blue black sky.

The dinner on Saturday night was terrific. The Saturn V center at KSC was an ideal venue. Ran into real and virtual friends including Larry, Noah, Jason, Mike & Miranda, Robert, Steve, Mark, and others.

I was lucky to sit at Gene Cernan’s table and enjoyed his stories of landing on the moon and his thoughts at being “the Last Man on the Moon.”

Flown Altimeter Plug from Apollo 12

The Altimeter in the Apollo CM (panel 1) was operational below 50,000 feet. Therefore it was only used by the crew during the early stages of initial powered ascent and then again at the very end of the mission. For the rest of the mission the altimeter was typically covered by an aluminum stopper.

This stopper was flown to the moon on the Apollo 12 mission. It was acquired from the personal collection of Apollo 12 Command Module Pilot Dick Gordon.

The accelerometer (G-force meter) was also only used in the early and late parts of the mission and had a similar, but slightly smaller, stopper.

Apollo CSM Guidance Computer Compensation Module

This module is a component of the Apollo CSM guidance computer and manufactured by AC Electronics. Anyone know more details about what this component did?

Moon Rock Container from the Lunar Receiving Laboratory

This lunar material container was used during the Apollo Era to transport and store moon rocks from the Lunar Receiving Laboratory. It is amazingly engineered, stainless steel vessel with bolts to secure the lunar sample to prevent contamination.

The accompanying tag, which was sealed in the bag that this container came in, indicates that it was cleaned in 1971 indicating that at one time it contained rocks from Apollo 11 and / or Apollo 12.

The Bolt-Top Container (BTC) was the primary storage and transport device used for lunar material. The BTC held a vacuum of pure nitrogen gas, which is inert and does not react with the lunar material inside.

This BTC was received by me in it's original double sealed vacuum bag. This is the first time this BTC has seen the day of light in over 35 years. The last person to handle this artifact was a lunar scientist in the LRL. These artifacts were sterilized after use and vacuum sealed for future use. Rigorous procedures were used to sterilize BTCs before being transfered into various cabinets in the LRL. The surface of the BTC was sprayed with peracetic acid in the R-102 (LRL atmospheric decontamination) cabinet . After 30 minutes of soak-time, the acid was removed by sterile water spray, then dried. This process provided biocidal sterilization without heat, as heat would alter the lunar material.

Thanks to Mike Bandli for the technical description of this artifact

Apollo 11 Parkway Viewing Site Vehicle Permit

Were you there? Alas, I was not.

Alan Bean sketch

Here is a fun little sketch of the CSM by artist and moonwalker Alan Bean (Apollo 12). I'll probably frame it, but I can't decide if I should include something else in the frame such as a mission photo.

Apollo CSM "Cobra Head" communications control assembly

This beautifully crafted communications control assembly was used for routing communications, biomedical signals, and warning tones. The control head, often referred to as a "Cobra Head" by the astronauts, allowed the astronaut to speak to crewmates over the intercom (I'COM) or to Houston (XMIT).  This example contains NASA stamps identification part numbers V56-715100-21 0632 and the serial number AAJ9360.

The photo of Apollo 17 astronauts Gene Cernan (left) and Ron Evans provide a fine example of what this artifact would have looked like in flight.

Thanks to John Fongheiser of Historic Space Systems the technical description of this artifact.

Lunar Module valve package assembly cable

This flight ready cable (single-end terminated with a connector) in its Bell Aerospace sealed packaging, would have connected to the pilot / shutoff valves on the Valve Package Assembly.  A bi-propellant valve assembly actually attached to the LM Ascent engine which controlled fuel and oxidizer flow to the engine.  You can see the cables installed on the engine in the photo.

Thanks to Scott Schneeweis for the technical description of this artifact.

Apollo Saturn V guidance and control computer logic circuit board

This artifact, a flight ready spare, was a critical part of the Saturn V guidance navigation and control computer system. The computer was housed in the Saturn V Instrument Unit, designed and built by IBM.

The computer and this board is of unusually light weight and was achieved by the use of magnesium-lithium alloy chassis, the first use of this alloy in structural fabrication for an electronics application and the lightest structural metal used in the aerospace industry.

The unit logic devices were produced as a wafers and a total of 8918 such wafers were mounted on dozens of pages in the computer. There is a green insulated connector that has gold pins.  This artifact is labeled: 6111774 SERIAL NUMBER 3 and the back side reads: 6112680 35-2 B SIDE.

Saturn V 1/200 scale model by Nick Proach

This model is a very accurate, hand carved (from mahogany) and painted representation of the Saturn V rocket. The vehicle model stands 23.5" tall including the base.  This exquisite model, made by Nick Proach Models, is fully licensed by Boeing, McDonnell-Douglas and North American Aviation.

Saturn V Instrument Unit directional CCS PCM antenna cover

This funky looking item is a Saturn V Instrument Unit directional CCS/PCM Antenna array cover. 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 is made of RF transparent epoxy impregnated fiberglass. The antenna cover 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 antenna it covered was a transmit only high gain directional antenna fixed on the IU with the radiation pattern was directed toward the earth by controlling the attitude of the spacecraft. The antenna contained 5 helical elements, 4 in quadrapole arrangement for high gain UHF S-BAND (2282.5 MHZ @ 20 watts) and 1 monopole element. 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.

Thanks to Scott Schneeweis for the technical description of this artifact.

Apollo Saturn V Launch Vehicle Electronic Analog Control Circuit Board

This artifact, a flight ready spare, was designed at the Marshall Space Flight Center in Huntsville, Alabama for the Saturn V flight control system.

It consists of 10 Texas Instruments gold base metal hermetically sealed transistors, 20 glass Zener diodes, and 20 Allen Bradley carbon composition resistors. The back of the circuit board contains electrical connector pins using gold in their construction. The high strength fiberglass circuit board is coated to protect the components from the environment.

The multipin interface connector has a triangular NASA certification stamp and 50M65845-1 designates the original designer as MSFC for the Apollo Saturn moon program. The dimensions are about 4.125 inches by 3.45 inches.

Apollo 15 beta cloth patch Lucite display

This interesting Lucite display reads "FIRST MOTOR VEHICLE DRIVEN ON THE MOON. Fiberglass materials continue to play an important role in man’s exploration of space—from textiles in fire-safe suits, to reinforcement applications in the lunar and command modules and now in the Lunar Roving Vehicle. Owens Corning Fiberglas. July 30 to August 2, 1971."

Apollo Spacesuit Hose Connector to CSM

This is an Apollo Command Module spacesuit suit hose connector used to connect to the CM bulkhead panel for suit oxygen and return.

The serial number on it are:

G14-824333

104-66 NC

06362 MAE2143

Chariots for Apollo: A history of manned lunar space missions

Chariots for Apollo: A history of manned lunar space missions (by Courtney G. Brooks, James M. Grimwood, and Loyd S. Swenson, Jr., NASA History Series SP-4205, first edition, 1979) is the definitive NASA account of the Apollo program.

This was the personal copy of Laurence K. Loftin, Jr. In 1970 Loftin held the position of Director for Aeronautics at the Langley Research Center and he was chief Aeronautical Engineer at Langley from July 1972 until his retirement from NASA in December 1973.

Project Apollo mug

Nearly all of the common souvenirs and trinkets sold to tourists at the Kennedy Space Center during the time of Apollo are, well, let’s just say not that interesting. The stuff just looks cheap (at least to me).

This Project Apollo mug is different. It is shaped like the Apollo Command Module and has clean lines and interesting graphics. It will look classic even in a hundred years.