Constructing Jupiter Chrysler Corporation Missile Division, Warren, Michigan
Driving past the large warehouse-like buildings today along 16 Mile Road and Van Dyke Avenue in Warren, Michigan one would never expect that the nation’s first continuously successful IRBM missiles had been built there during the late 1950’s and early 1960’s!  This was the home of the Chrysler Corporation Missile Division’s (CCMD) Jupiter missile construction facilities. Edgar May was one of the division’s individuals who participated in the design/construction of Jupiter’s component parts. The following are photos with descriptions of various stages of construction throughout the plant as provided by Ed. [Note Mgr.’s lapel pin…the Chrysler icon, in those days the “forward” look!). Edgar W. May was born April 11,1931, graduated Edwin Denby High school Detroit, Michigan in June  of 1950. He was drafted into the U. S. Army December 1951, spent one year in the Infantry serving in Korea July 1952 to July 1953. Ed studied mechanical engineering at the University of Michigan, September 1954 to May 1957, finishing his degree at University of Detroit night school. Ed began working at (CCMD) Chrysler Corporation Missile Division on May the 27th, 1957. He married in February 1958 and was blessed with a daughter and a son. He began his career as an Engineering Tech Aide at CCMD, rising through the years to become a Senior Engineering Research Specialist. Ed worked at CCMD and Chrysler Defense Engineering for fourteen years with the exception of 15 months during the period between 1964-65 when he worked at Ling Temco Vought’s (LTV) Michigan Division with the Lance Missile Program.  While at CCMD Ed worked on many different programs starting with Redstone Missile R&D and then with production versions which were deployed in Germany during the Cold War. He worked on a program to add measuring components to production block two missile CC-2015 and participated in the launch at White Sands missile range in New Mexico in what was an Army ASP (Annual Service Practice) launch. After  Redstone was retired from Army service they modified several to be launched from San Nicolas Island off the California coast as targets for a Navy antimissile program called DAT (Data Acquisition Target). They also designed nine reentry vehicles for the Sparta Program which were launched on modified Redstones with an added second stage at the Woomera Missile Range in Australia. The 10th launch in this program put the first Australian satellite WRESAT-1 in orbit and it was the 100th and last launch of a Redstone Missile.  Ed was granted Top Secret AEC clearance with the Jupiter Missile program as a result of working with its nuclear Nose Cones. Some of his additional involvement with the Jupiter program were as follows:  1) Worked closely with ABMA for the installation of all instrumentation and inter-connecting cabling in the Aft Unit; 2) Stationary erection and de-erection system for missiles that were deployed in Europe; 3) Corrected design deficiencies and converted the proto-type definition of the Vertical Shelter into a production technical data package; and 4) A system to protect the missiles deployed in Italy from lightning strikes.  We thank Ed for his work, and for sharing through his contributions insights into what surely must have been one of the most interesting careers during some of the most turbulent times times of American history.
#01.   [32491:   10/22/58]   Looking   into   the   tip   of   a   Jupiter   nosecone   where   you can see the three impact fuses.
Ed May (Left), Dept. Manager (R), 4/14/1959.  [CCMD, Ed May] Ed May (Left), Dept. Manager (R), 4/14/1959.  [CCMD, Ed May] Ed May (Left), Dept. Manager (R), 4/14/1959.  [CCMD, Ed May]
Ed May (L) & Dept. Manager 4/14/1959
Originally published:  03/24/2017 
Last updated:  01/21/2018  16:36
[60035: 6/27/1958] Re-entry vehicle, using wooden boxes to simulate actual components. Heavily instrumented for re-entry flight.  [CCMD, Ed May [60035: 6/27/1958] Re-entry vehicle, using wooden boxes to simulate actual components. Heavily instrumented for re-entry flight.  [CCMD, Ed May [60035: 6/27/1958] Re-entry vehicle, using wooden boxes to simulate actual components. Heavily instrumented for re-entry flight.  [CCMD, Ed May
#02.   [60035:   6/27/1958]   Re-entry   vehicle,   using   wooden   boxes   to   simulate actual components. Heavily instrumented for re-entry flight.
The   following   five   photographs   are   of   Jupiter   Missile   R&D   (Research   &   Development)   Nose   Cones   built   by CCMD   (Chrysler   Corporation   Missile   Division)   in   1959.   The   Nose   Cone   was   designed   to   deliver   on   target   a   W- 49   thermonuclear   1.45   mega   ton   bomb.   For   redundancy,   the   bomb   fuse   system   had   three   triggers:   the   first was   a   proximity   device   set   to   detonate   the   bomb   at   a   set   altitude   burst   for   maximum   target   destruction. Secondly,   if   that   did   not   work   a   timer   started   at   Nose   Cone   separation   from   the   Aft   Unit   would   detonate   the bomb,   and   thirdly   if   those   two   failed   there   were   impact   triggers   set   to   fire   at   ground   contact.   The   impact triggers can be seen on the inside tip of the Nose Cone shown in photo 32491. The   scientists   and   engineers   at   the   Army   Ballistic   Missile   Agency   (ABMA)   in   Huntsville,   Alabama   came   up with   an   ingenious   way   to   protect   the   aluminum   body   of   the   Nose   Cone   from   the   2000-degree   frictional   heat of   reentry   into   the   earth’s   atmosphere.   They   coated   the   body   with   a   ceramic   material   that   ablated   away   to throw   off   the   reentry   heat.   It   was   two   and   one   half   inches   thick   at   the   tip   of   the   Nose   Cone   and   tapered   to one half inch at the rear of the Cone. Photo   60035   is   a   view   looking   into   a   heavily   instrumented   Nose   Cone   for   measuring   in   flight   and   reentry parameters   and   bomb   triggering   performance.   Some   of   the   instrument   boxes   are   wooden   mock   ups   at   this stage of assembly. Photos    62936,62937    and    62938    are    three    views    of    another    Nose    Cone    during    assemble    the    two    black longitudinal   shapes   in   photo   62937   on   the   right   side   of   the   Nose   Cone   are   two   of   the   four   telemetry antennas for transmitting measurement data to ground stations. Note   in   the   right   side   of   photo   62938   on   a   work   stand   is   the   nozzle   of   a   Rocketdyne      Model   S-3D   150 thousand pound thrust rocket engine.

NOSE CONE

AFT

The   following   18   photographs   are   of   Jupiter   Missile   R&D   Aft   Units   built   by   CCMD   in   1958   and   1959.   The   Aft Unit   was   mounted   away   from   and   on   top   of   the   Thrust   Unit.   The   Thrust   Unit   consisted   of   propellant   tanks and    the    [Rocketdyne]    rocket    engine.    The    Aft    Unit    provided    vernier    adjustments    for    flight    trajectory. Contained   within   the   conical   Aft   Unit   was   the   inertial   guidance   and   control   (G&C)   instrumentation   that provided   guidance   from   launch   to   Nose   Cone   designated   target.      Attached   to   the   front   end   of   the   Aft   Unit was the Nose Cone. The Aft Unit and Nose Cone together are called the Body Unit. Photo   73697   is   a   view   looking   into   the   front   of   an   Aft   Unit   sitting   on   a   factory   work   stand.   On   the   right   in   the photo   marked   Army   is   the   Thrust   Unit   of   a   Redstone   Missile   also   built   by   CCMD.   For   orientation,   the   four compartments   formed   by   the   X   crossed   instrument   panels   will   be   referred   to   as   quadrants   with   number   one at the top and clockwise to quadrant number four. The   ST-90   stable   platform   was   mounted   in   quadrant   one   floating   in   a   stable   position   with   respect   to   the earth.    With    a    system    of    gyroscopes    and    accelerometers    the    ST-90    would    measure    deviations    in    three- dimensional   space   from   the   missile’s   programed   flight   path,   then   provide   this   data   to   other   instruments which created and provided corrections to maintain the Nose Cone on its programed course to target. The   word   CAUTION   is   marked   on   the   aft   bulkhead   which   with   the   Nose   Cone   attached   to   the   front   of   the   Aft Unit sealed the instrument compartment to atmospheric pressure. A   small   500   pound   thrust   rocket   located   in   the   rear   of   the   Aft   Unit   would   be   fired   to   move   the   Aft   Unit   away from   the   Thrust   Unit   to   prevent   its   forward   momentum   from   colliding   with   the   Body   Unit   after   Thrust   Unit separation.    Upon    attaining    ballistic    flight    path’s    apogee    the    Body    Unit    would    be    oriented    in    the    same attitude in which it had left the atmosphere. Spatial   attitude   control   high   pressure   jets   in   the   Aft   Unit   would   be   fired   causing   the   Body   Unit   to   tilt   so   that the   Nose   Cone   would   be   pointed   down   toward   the   earth,   at   which   time   the   Aft   Unit’s   Spin   Rockets   would   be fired   adding   Nose   Cone   ballistic   stability   during   the   remainder   of   its   flight   to   target.   The   Nose   Cone   would then   be   separated   from   the   Aft   Unit   by   detonating   primer   cord   wrapped   around   the   bolts   attaching   the Nose   Cone   to   the   Aft   unit.   The   Instrument   Compartment’s   atmospheric   pressure   would   push   the   two   units apart thus ensuring the Aft Unit would not interfere with the Nose Cone. Pitot   Tubes,   extended   during   countdown,   were   mounted   in   the   four   cylindrical   items   at   the   outer   skin   of each    quadrant    thus    providing    four    independent    airspeed    data    streams    to    the    Guidance    and    Control package. (see Photo 73697). Ed   was   working   in   CCMD’s   Department   7262,   “Electro-Mechanical   Design,”   during   the   years   1958-1959   when many of these photos were taken.
[62936: 8/12/1959] Re-entry vehicle, using wooden boxes to similate actual components. Heavily instrumented for re-entry flight.  [CCMD, Ed May] [62936: 8/12/1959] Re-entry vehicle, using wooden boxes to similate actual components. Heavily instrumented for re-entry flight.  [CCMD, Ed May] [62936: 8/12/1959] Re-entry vehicle, using wooden boxes to similate actual components. Heavily instrumented for re-entry flight.  [CCMD, Ed May]
#03.   [62936:   8/12/1959]   Re-entry   vehicle,   using   wooden   boxes   to   simulate actual components. Heavily instrumented for re-entry flight.
[73697: 3/3/1960]  Looking into top of Guidance Package, the Aft Unit (was mounted to main body, on top of fuel tanks), located just behind the warhead. Explosive bolts would separate re-entry vehicle. Right is shown a Redstone Missile (Tactical Missile). [73697: 3/3/1960]  Looking into top of Guidance Package, the Aft Unit (was mounted to main body, on top of fuel tanks), located just behind the warhead. Explosive bolts would separate re-entry vehicle. Right is shown a Redstone Missile (Tactical Missile). [73697: 3/3/1960]  Looking into top of Guidance Package, the Aft Unit (was mounted to main body, on top of fuel tanks), located just behind the warhead. Explosive bolts would separate re-entry vehicle. Right is shown a Redstone Missile (Tactical Missile).
#06   [73697:   3/3/1960]      Looking   into   top   of   Guidance   Package,   the   Aft   Unit (was   mounted   to   main   body,   on   top   of   fuel   tanks),   located   just   behind   the warhead.   Explosive   bolts   would   separate   re-entry   vehicle.   Right   is   shown   a Redstone Missile (Tactical Missile).
[62938: 8/12/1959]  Re-entry vehicle, using wooden boxes to similate actual components. Heavily instrumented for re-entry flight. To the right of the re-entry vehicle is an Engine Thrust Chamber.  [CCMD, Ed May] [62938: 8/12/1959]  Re-entry vehicle, using wooden boxes to similate actual components. Heavily instrumented for re-entry flight. To the right of the re-entry vehicle is an Engine Thrust Chamber.  [CCMD, Ed May] [62938: 8/12/1959]  Re-entry vehicle, using wooden boxes to similate actual components. Heavily instrumented for re-entry flight. To the right of the re-entry vehicle is an Engine Thrust Chamber.  [CCMD, Ed May]
#05.   [62938:   8/12/1959]      Re-entry   vehicle,   using   wooden   boxes   to   simulate actual   components.   Heavily   instrumented   for   re-entry   flight.   To   the   right   of the re-entry vehicle is an Engine Thrust Chamber.
[62937: 8/12/1959]  Re-entry vehicle, using wooden boxes to similate actual components. Heavily instrumented for re-entry flight.  [CCMD, Ed May] [62937: 8/12/1959]  Re-entry vehicle, using wooden boxes to similate actual components. Heavily instrumented for re-entry flight.  [CCMD, Ed May] [62937: 8/12/1959]  Re-entry vehicle, using wooden boxes to similate actual components. Heavily instrumented for re-entry flight.  [CCMD, Ed May]
#04.   [62937:   8/12/1959]      Re-entry   vehicle,   using   wooden   boxes   to   simulate actual    components.    Heavily    instrumented    for    re-entry    flight.    The    black “stripes”     around     the     nose     cone’s     outside     perimeter     are     telemetry antennas.
#22   [21108:   5/5/58]   Very   early   mockup   looking   into   quadrant   3   most   of   the instruments are wooden mockups of the real items.
[32491: 10/22/58] Looking into a real Jupiter warhead, showing impact fuse which exists in addition to a proximity fuse. There was also an electronic fuse (time into flight?)  [CCMD, Ed May] [32491: 10/22/58] Looking into a real Jupiter warhead, showing impact fuse which exists in addition to a proximity fuse. There was also an electronic fuse (time into flight?)  [CCMD, Ed May] [32491: 10/22/58] Looking into a real Jupiter warhead, showing impact fuse which exists in addition to a proximity fuse. There was also an electronic fuse (time into flight?)  [CCMD, Ed May] [21108: 5/5/58] Early mockup, parts simulated with wooden parts. Some parts were real. Wires go to dummy connectors.  [CCMD, Ed May] [21108: 5/5/58] Early mockup, parts simulated with wooden parts. Some parts were real. Wires go to dummy connectors.  [CCMD, Ed May] [21108: 5/5/58] Early mockup, parts simulated with wooden parts. Some parts were real. Wires go to dummy connectors.  [CCMD, Ed May] [69864: 12/7/1959]  Looking into another quadrant, empty. Instrument compartment was in an "X" configuration.  [CCMD, Ed May] [69864: 12/7/1959]  Looking into another quadrant, empty. Instrument compartment was in an "X" configuration.  [CCMD, Ed May] [69864: 12/7/1959]  Looking into another quadrant, empty. Instrument compartment was in an "X" configuration.  [CCMD, Ed May]
#07.   [69864:   12/7/1959]      View   looking   into   quadrant   1   during   an   early   stage of   assembly.   The   Aft   Unit   had   hatch   openings   in   each   quadrant   to   provide excess   for   the   installation   of   the   instrumentation   and   were   covered   with hatch   panels   at   final   assembly.   In   the   field   the   hatches   could   be   opened   for any necessary repairs
[69865: 12/7/1959]  Looking into another quadrant. The "ball joint" device is an attachment point for the ST-90 Stabilization Platform. Sheet metal cover over the exposed vertical bracket used for cooling around stabilization platform.  [CCMD, Ed May] [69865: 12/7/1959]  Looking into another quadrant. The "ball joint" device is an attachment point for the ST-90 Stabilization Platform. Sheet metal cover over the exposed vertical bracket used for cooling around stabilization platform.  [CCMD, Ed May] [69865: 12/7/1959]  Looking into another quadrant. The "ball joint" device is an attachment point for the ST-90 Stabilization Platform. Sheet metal cover over the exposed vertical bracket used for cooling around stabilization platform.  [CCMD, Ed May]
#08.   [69865:   12/7/1959]      Looking   also   into   quadrant   1.   The   "ball   joint"   in   the lower    left    corner    is    an    attachment    point    for    the    ST-90    Stabilization Platform.   The   sheet   metal   structure   with   the   row   of   attaching   points   is   the mounting   surface   for   the   cover   placed   over   the   ST-90   to   reduce   the   volume to be cooled.
[69866: 12/7/1959]  Looing into quadrant where the SD-90 was mounted. Can see the cover. SD-90 is the inertial guidance stabilization platform. [CCMD, Ed May] [69866: 12/7/1959]  Looing into quadrant where the SD-90 was mounted. Can see the cover. SD-90 is the inertial guidance stabilization platform. [CCMD, Ed May] [69866: 12/7/1959]  Looing into quadrant where the SD-90 was mounted. Can see the cover. SD-90 is the inertial guidance stabilization platform. [CCMD, Ed May]
#09: [69866: 12/7/1959]  Close up view of the ST-90 " ball joint" attachment.
[69867: 12/7/1959]  Looking to SD-90 Quadrant. EO=Engineering Order.  [CCMD, Ed May] [69867: 12/7/1959]  Looking to SD-90 Quadrant. EO=Engineering Order.  [CCMD, Ed May] [69867: 12/7/1959]  Looking to SD-90 Quadrant. EO=Engineering Order.  [CCMD, Ed May]
#10:   [69867:   12/7/1959]      In   quadrant   1   the   white   marking   on   the   black   ST-90 mounting   ring   are   to   indicate   the   latest   engineering   change   order   (EO) incorporated into the part.
[70239: 12/10/1959]  Showing Stable Platform Mounting Bracket, full yoke. Cooling fan blowers at top and bottom.  [CCMD, Ed May] [70239: 12/10/1959]  Showing Stable Platform Mounting Bracket, full yoke. Cooling fan blowers at top and bottom.  [CCMD, Ed May] [70239: 12/10/1959]  Showing Stable Platform Mounting Bracket, full yoke. Cooling fan blowers at top and bottom.  [CCMD, Ed May]
#11.   [70239:   12/10/1959]      Looking   straight   into   quadrant   1.   The   squared shaped   structure   is   the   mounting   ring   for   the   ST-90.   At   the   bottom   of   the   V is   the   300   CFM   blower   and   vents   to   circulate   cool   air   over   the   ST-90   during flight.
[70240: 12/10/1959]  Showing Stable Platform Mounting Bracket, full yoke. Cooling fan blowers at bottom and inside. R/S Electrical Connectors covered during assembly to keep out dirt.  [CCMD, Ed May] [70240: 12/10/1959]  Showing Stable Platform Mounting Bracket, full yoke. Cooling fan blowers at bottom and inside. R/S Electrical Connectors covered during assembly to keep out dirt.  [CCMD, Ed May] [70240: 12/10/1959]  Showing Stable Platform Mounting Bracket, full yoke. Cooling fan blowers at bottom and inside. R/S Electrical Connectors covered during assembly to keep out dirt.  [CCMD, Ed May]
#12.   [70240:   12/10/1959]      Showing   Stable   Platform   Mounting   Bracket,   full yoke.   Cooling   fan   blowers   at   bottom   and   inside.   R/S   Electrical   Connectors covered during assembly to keep out dirt.
[33816: 11/03/58] Instrument panels are made out of plywood. Developed honeycomb aluminum, R&D Warhead early in program. Two cutouts show 2ea antennas telemetry.  [CCMD, Ed May] [33816: 11/03/58] Instrument panels are made out of plywood. Developed honeycomb aluminum, R&D Warhead early in program. Two cutouts show 2ea antennas telemetry.  [CCMD, Ed May] [33816: 11/03/58] Instrument panels are made out of plywood. Developed honeycomb aluminum, R&D Warhead early in program. Two cutouts show 2ea antennas telemetry.  [CCMD, Ed May]
#21.   [33816:   11/03/58]   View   looking   into   quadrant   4   of   a   very   early   R&D   Aft Unit.     Note     that     the     instrumental     panels     are     plywood.     Developed honeycomb   aluminum,   R&D   Warhead   early   in   program.   Two   cutouts   show 2ea antennas telemetry.
#13.   [69862:   12/7/1959]      View   looking   at   the   right-side   instrument   panel   of quadrant   2.   R&D   missiles   used   plywood   instrument   panel   but   for   weight reduction   production   units   used   honeycombed   aluminum.   The   large   tank held    in    place    with    the    two    metal    straps    is    the    Ln2    (liquid    nitrogen) container   for   the   in-flight   cooling   system.   It   is   wrapped   with   insulation held   in   place   with   duct   tape.   The   corrugated   tubing at   the   right   side   is   for   the   exterior   pre-fight   cooling system.
[69862: 12/7/1959]  Aft Unit Instrumentation, using honeycombed Aluminum mounting surfaces. Liquid Nitrogen in-flight cooling tank. Wrapped with insulation, wrapped with duct tape to hold in place.  [CCMD, Ed May] [69862: 12/7/1959]  Aft Unit Instrumentation, using honeycombed Aluminum mounting surfaces. Liquid Nitrogen in-flight cooling tank. Wrapped with insulation, wrapped with duct tape to hold in place.  [CCMD, Ed May
[69869: 12/7/1959]  Looking into another quadrant; shows honeycomb aluminum mounting panel. Part of guidance, "Program Device," made by Ford.  [CCMD, Ed May] [69869: 12/7/1959]  Looking into another quadrant; shows honeycomb aluminum mounting panel. Part of guidance, "Program Device," made by Ford.  [CCMD, Ed May] [69869: 12/7/1959]  Looking into another quadrant; shows honeycomb aluminum mounting panel. Part of guidance, "Program Device," made by Ford.  [CCMD, Ed May]
#18:    [69869:    12/7/1959]        The    Flight    Programmer    is    mounted    on    the    left instrument   panel   of   quadrant   4.   The   Ln2   fill   tube   passes   thru   the   panel across   the   top   of   quadrant   1   thru   the   right   panel   of   quadrant   2   and   into the Ln2 tank. At the top of the photo is the extendible pitot tube canister.  
#19.   [33824:   11/03/58]   The   rear   end   of   an   Aft   Unit   sitting   on   a   factory   work stand.    At    the    left    is    one    of    the    fiber    glass    spheres    that    held    the    high- pressure air for the spatial attitude control system.
[33824: 11/03/58] Looking at the bottom of the G&C package. Sphere is fiberglass for high pressure air, tested to 7500psi, Flight Tested to 3,000 psi. Spatial Directional Countrol.  [CCMD, Ed May] [33824: 11/03/58] Looking at the bottom of the G&C package. Sphere is fiberglass for high pressure air, tested to 7500psi, Flight Tested to 3,000 psi. Spatial Directional Countrol.  [CCMD, Ed May] [33824: 11/03/58] Looking at the bottom of the G&C package. Sphere is fiberglass for high pressure air, tested to 7500psi, Flight Tested to 3,000 psi. Spatial Directional Countrol.  [CCMD, Ed May] #20: [33826: 11/03/58]  #19: [33824: (11/3/1958)] Thrust Unit electric cables would be connected to the five connectors shown for the transmission of signals such as rocket engine gimbling instructions for directional control, burn time and Thrust Unit separation command. At this point of assembly, the 500 pound Vernier rocket motor is not yet installed. [33826: 11/03/58]  Another view of the G&C package. Six electrical connectors feed propulsion unit (fuel tanks, engine).  [CCMD, Ed May] [33826: 11/03/58]  Another view of the G&C package. Six electrical connectors feed propulsion unit (fuel tanks, engine).  [CCMD, Ed May] [33826: 11/03/58]  Another view of the G&C package. Six electrical connectors feed propulsion unit (fuel tanks, engine).  [CCMD, Ed May]
#14.   [69863:   12/7/1959]      View   looking   at   the   left   side   instrument   panel   of quadrant    2.    Aft    Unit    Instrumentation,    using    honeycombed    Aluminum mounting   surfaces.   Liquid   Nitrogen   in-flight   cooling   tank.   Wrapped   with insulation, wrapped with duct tape to hold in place.
[69863: 12/7/1959]  Aft Unit Instrumentation, using honeycombed Aluminum mounting surfaces. Liquid Nitrogen in-flight cooling tank. Wrapped with insulation, wrapped with duct tape to hold in place.  [CCMD, Ed May] [69863: 12/7/1959]  Aft Unit Instrumentation, using honeycombed Aluminum mounting surfaces. Liquid Nitrogen in-flight cooling tank. Wrapped with insulation, wrapped with duct tape to hold in place.  [CCMD, Ed May] [69863: 12/7/1959]  Aft Unit Instrumentation, using honeycombed Aluminum mounting surfaces. Liquid Nitrogen in-flight cooling tank. Wrapped with insulation, wrapped with duct tape to hold in place.  [CCMD, Ed May] [73698: 3/3/1960]  Top of Liquid Nitrogen Cooling Tank, showing flex tubing that routes cool air to G&C package. Aluminum tubing was high pressure air feeding tank to circulate nitro for cooling.  [CCMD, Ed May] [73698: 3/3/1960]  Top of Liquid Nitrogen Cooling Tank, showing flex tubing that routes cool air to G&C package. Aluminum tubing was high pressure air feeding tank to circulate nitro for cooling.  [CCMD, Ed May] [73698: 3/3/1960]  Top of Liquid Nitrogen Cooling Tank, showing flex tubing that routes cool air to G&C package. Aluminum tubing was high pressure air feeding tank to circulate nitro for cooling.  [CCMD, Ed May]
#15.   [73698:   3/3/1960]      View   looking   at   the   top   of   the   Ln2   tank.   The   three corrugated    tubes    are    for    routing    cooled    air    from    the    tank    into    other quadrants.   The   Ln2   is   pumped   into   the   tank   during   countdown   through   the small tube elbowed down into the tank. 
[69868: 12/7/1959]  Black box is a 400cps Inverter, converted 28vdc DC to 400Hz AC. Unit 300cf/s cooling source was taped off.  [CCMD, Ed May] [69868: 12/7/1959]  Black box is a 400cps Inverter, converted 28vdc DC to 400Hz AC. Unit 300cf/s cooling source was taped off.  [CCMD, Ed May] [69868: 12/7/1959]  Black box is a 400cps Inverter, converted 28vdc DC to 400Hz AC. Unit 300cf/s cooling source was taped off.  [CCMD, Ed May]
#16.    [69868:    12/7/1959]        View    looking    into    quadrant    3    under    the    black instrument   (which   is   an   inverter   for   converting   28-volt   DC   into   400Hz   AC)   is the blower for the preflight cooling system.
[69870: 12/7/1959]  Looking into 4th quadrant, tubing covered with tape was part of cooling system.  [CCMD, Ed May] [69870: 12/7/1959]  Looking into 4th quadrant, tubing covered with tape was part of cooling system.  [CCMD, Ed May] [69870: 12/7/1959]  Looking into 4th quadrant, tubing covered with tape was part of cooling system.  [CCMD, Ed May]
#17.   [69870:   12/7/1959]      View   looking   into   quadrant   4.   The   duck   tapped tubing is the line for filling the Ln2 tank during countdown.

GROUND CONTROL EQUIPMENT

The   human   interface   to   the   Jupiter   missile   came   through   the   Launch   Consoles   contained   within   the   Launch Trailers. The following five photos show the Launch Trailer and their console’s initial configuration.
[71890: 1/28/1960]  Launch Control Trailer Schematic.  [CCMD, Ed May] [71890: 1/28/1960]  Launch Control Trailer Schematic.  [CCMD, Ed May] [71890: 1/28/1960]  Launch Control Trailer Schematic.  [CCMD, Ed May]
#23.   [71890:   1/28/1960]      Floor   plan   of   the   Electrical   Equipment   Trailer   which was used to run periodic checkups of all missile instrumentation.
[49597, 6/18/1959] Chrysler R&D Missile; CM AP initials:  C= Chrysler  M=Missile  AP?=21  = Chrysler Missile 21.  [CCMD, Ed May] [49597, 6/18/1959] Chrysler R&D Missile; CM AP initials:  C= Chrysler  M=Missile  AP?=21  = Chrysler Missile 21.  [CCMD, Ed May] [49597, 6/18/1959] Chrysler R&D Missile; CM AP initials:  C= Chrysler  M=Missile  AP?=21  = Chrysler Missile 21.  [CCMD, Ed May]
#28.   [49597;   6/18/1959]   Chrysler   R&D   Missile;   CM   AP   initials:      C=   Chrysler     M=Missile      AP?=21      =   Chrysler   Missile   21   [for   reasons   of   security   to   conceal the   number   of   the   missile   a   word   was   used   maybe   in   this   case   Able   B   for   2 and A for 1.]
[47148: 05/06/1959]  Inside Launch Trailer.  [CCMD, Ed May] [47148: 05/06/1959]  Inside Launch Trailer.  [CCMD, Ed May] [47148: 05/06/1959]  Inside Launch Trailer.  [CCMD, Ed May]
#24.   [47148:   05/06/1959]      View   looking   aft   in   the   Launch   Control Trailer.
[47147: 05/06/1959]  Launch Console for 3 missiles. One display for each of the 3 site missiles.  [CCMD, Ed May] [47147: 05/06/1959]  Launch Console for 3 missiles. One display for each of the 3 site missiles.  [CCMD, Ed May] [47147: 05/06/1959]  Launch Console for 3 missiles. One display for each of the 3 site missiles.  [CCMD, Ed May]
#27. [47147: 05/06/1959]  Close up view of the Launch Control Console.
[43361: 03/10/1959]  Juno Missile, moon shot or placing object in orbit? Cooling tower falling away on right side.  [CCMD, Ed May] [43361: 03/10/1959]  Juno Missile, moon shot or placing object in orbit? Cooling tower falling away on right side.  [CCMD, Ed May] [43361: 03/10/1959]  Juno Missile, moon shot or placing object in orbit? Cooling tower falling away on right side.  [CCMD, Ed May]
#29.   [43361:   03/10/1959]      Juno   Missile,   moon   shot   or   placing   object   in   orbit? Cooling tower falling away on right side.
[44647: 04/02/1959]  Inside Launch Trailer. Launch Console was forward in trailer.  [CCMD, Ed May] [44647: 04/02/1959]  Inside Launch Trailer. Launch Console was forward in trailer.  [CCMD, Ed May] [44647: 04/02/1959]  Inside Launch Trailer. Launch Console was forward in trailer.  [CCMD, Ed May]
#25. [44647: 04/02/1959]  Also looking aft in the Launch Control Trailer.
[29998: 9/22/58] Launch Console for 3 missiles. One display for each of the 3 site missiles. [CCMD, Ed May] [29998: 9/22/58] Launch Console for 3 missiles. One display for each of the 3 site missiles. [CCMD, Ed May] [29998: 9/22/58] Launch Console for 3 missiles. One display for each of the 3 site missiles. [CCMD, Ed May]
#26.   [29998:   9/22/58]   Launch   Control   Console,   one   panel   for   each   of   the three missiles on the launch site.
Jupiter’s Ground Equipment Ed May
Made with Xara Driving past the large warehouse-like buildings today along 16 Mile Road and Van Dyke Avenue in Warren, Michigan one would never expect that the nation’s first continuously successful IRBM missiles had been built there during the late 1950’s and early 1960’s!  This was the home of the Chrysler Corporation Missile Division’s (CCMD) Jupiter missile construction facilities. Edgar May was one of the division’s individuals who participated in the design/construction of Jupiter’s component parts. The following are photos with descriptions of various stages of construction throughout the plant as provided by Ed. [Note Mgr.’s lapel pin…the Chrysler icon, in those days the “forward” look!). Edgar W. May was born April 11,1931, graduated Edwin Denby High school Detroit, Michigan in June  of 1950. He was drafted into the U. S. Army December 1951, spent one year in the Infantry serving in Korea July 1952 to July 1953. Ed studied mechanical engineering at the University of Michigan, September 1954 to May 1957, finishing his degree at University of Detroit night school. Ed began working at (CCMD) Chrysler Corporation Missile Division on May the 27th, 1957. He married in February 1958 and was blessed with a daughter and a son. He began his career as an Engineering Tech Aide at CCMD, rising through the years to become a Senior Engineering Research Specialist. Ed worked at CCMD and Chrysler Defense Engineering for fourteen years with the exception of 15 months during the period between 1964-65 when he worked at Ling Temco Vought’s (LTV) Michigan Division with the Lance Missile Program.  While at CCMD Ed worked on many different programs starting with Redstone Missile R&D and then with production versions which were deployed in Germany during the Cold War. He worked on a program to add measuring components to production block two missile CC-2015 and participated in the launch at White Sands missile range in New Mexico in what was an Army ASP (Annual Service Practice) launch. After  Redstone was retired from Army service they modified several to be launched from San Nicolas Island off the California coast as targets for a Navy antimissile program called DAT (Data Acquisition Target). They also designed nine reentry vehicles for the Sparta Program which were launched on modified Redstones with an added second stage at the Woomera Missile Range in Australia. The 10th launch in this program put the first Australian satellite WRESAT-1 in orbit and it was the 100th and last launch of a Redstone Missile.  Ed was granted Top Secret AEC clearance with the Jupiter Missile program as a result of working with its nuclear Nose Cones. Some of his additional involvement with the Jupiter program were as follows:  1) Worked closely with ABMA for the installation of all instrumentation and inter-connecting cabling in the Aft Unit; 2) Stationary erection and de-erection system for missiles that were deployed in Europe; 3) Corrected design deficiencies and converted the proto-type definition of the Vertical Shelter into a production technical data package; and 4) A system to protect the missiles deployed in Italy from lightning strikes.  We thank Ed for his work, and for sharing through his contributions insights into what surely must have been one of the most interesting careers during some of the most turbulent times times of American history. Ed May (Left), Dept. Manager (R), 4/14/1959.  [CCMD, Ed May] Ed May (Left), Dept. Manager (R), 4/14/1959.  [CCMD, Ed May] Ed May (Left), Dept. Manager (R), 4/14/1959.  [CCMD, Ed May]
Ed May (L) & Dept. Manager 4/14/1959
Ed May

NOSE CONE

The    following    five    photographs    are    of    Jupiter    Missile    R&D (Research   &   Development)   Nose   Cones   built   by   CCMD   (Chrysler Corporation    Missile    Division)    in    1959.    The    Nose    Cone    was designed   to   deliver   on   target   a   W-49   thermonuclear   1.45   mega ton   bomb.   For   redundancy,   the   bomb   fuse   system   had   three triggers:   the   first   was   a   proximity   device   set   to   detonate   the bomb   at   a   set   altitude   burst   for   maximum   target   destruction. Secondly,   if   that   did   not   work   a   timer   started   at   Nose   Cone separation   from   the   Aft   Unit   would   detonate   the   bomb,   and thirdly   if   those   two   failed   there   were   impact   triggers   set   to   fire at    ground    contact.    The    impact    triggers    can    be    seen    on    the inside tip of the Nose Cone shown in photo 32491. The    scientists    and    engineers    at    the    Army    Ballistic    Missile Agency    (ABMA)    in    Huntsville,    Alabama    came    up    with    an ingenious   way   to   protect   the   aluminum   body   of   the   Nose   Cone from   the   2000-degree   frictional   heat   of   reentry   into   the   earth’s atmosphere.    They    coated    the    body    with    a    ceramic    material that   ablated   away   to   throw   off   the   reentry   heat.   It   was   two and    one    half    inches    thick    at    the    tip    of    the    Nose    Cone    and tapered to one half inch at the rear of the Cone. Photo   60035   is   a   view   looking   into   a   heavily   instrumented   Nose Cone   for   measuring   in   flight   and   reentry   parameters   and   bomb triggering    performance.    Some    of    the    instrument    boxes    are wooden mock ups at this stage of assembly. Photos   62936,62937   and   62938   are   three   views   of   another   Nose Cone    during    assemble    the    two    black    longitudinal    shapes    in photo   62937   on   the   right   side   of   the   Nose   Cone   are   two   of   the four   telemetry   antennas   for   transmitting   measurement   data to ground stations. Note   in   the   right   side   of   photo   62938   on   a   work   stand   is   the nozzle   of   a   Rocketdyne      Model   S-3D   150   thousand   pound   thrust rocket engine.
[32491: 10/22/58] Looking into a real Jupiter warhead, showing impact fuse which exists in addition to a proximity fuse. There was also an electronic fuse (time into flight?)  [CCMD, Ed May] [32491: 10/22/58] Looking into a real Jupiter warhead, showing impact fuse which exists in addition to a proximity fuse. There was also an electronic fuse (time into flight?)  [CCMD, Ed May] [32491: 10/22/58] Looking into a real Jupiter warhead, showing impact fuse which exists in addition to a proximity fuse. There was also an electronic fuse (time into flight?)  [CCMD, Ed May]
#01.   [32491:   10/22/58]   Looking   into   the   tip   of   a Jupiter   nosecone   where   you   can   see   the   three impact fuses.
[60035: 6/27/1958] Re-entry vehicle, using wooden boxes to simulate actual components. Heavily instrumented for re-entry flight.  [CCMD, Ed May [60035: 6/27/1958] Re-entry vehicle, using wooden boxes to simulate actual components. Heavily instrumented for re-entry flight.  [CCMD, Ed May [60035: 6/27/1958] Re-entry vehicle, using wooden boxes to simulate actual components. Heavily instrumented for re-entry flight.  [CCMD, Ed May
#02.   [60035:   6/27/1958]   Re-entry   vehicle,   using wooden   boxes   to   simulate   actual   components. Heavily instrumented for re-entry flight.
[62936: 8/12/1959] Re-entry vehicle, using wooden boxes to similate actual components. Heavily instrumented for re-entry flight.  [CCMD, Ed May] [62936: 8/12/1959] Re-entry vehicle, using wooden boxes to similate actual components. Heavily instrumented for re-entry flight.  [CCMD, Ed May] [62936: 8/12/1959] Re-entry vehicle, using wooden boxes to similate actual components. Heavily instrumented for re-entry flight.  [CCMD, Ed May]
#03.   [62936:   8/12/1959]   Re-entry   vehicle,   using wooden   boxes   to   simulate   actual   components. Heavily instrumented for re-entry flight.
[62937: 8/12/1959]  Re-entry vehicle, using wooden boxes to similate actual components. Heavily instrumented for re-entry flight.  [CCMD, Ed May] [62937: 8/12/1959]  Re-entry vehicle, using wooden boxes to similate actual components. Heavily instrumented for re-entry flight.  [CCMD, Ed May] [62937: 8/12/1959]  Re-entry vehicle, using wooden boxes to similate actual components. Heavily instrumented for re-entry flight.  [CCMD, Ed May]
#04.   [62937:   8/12/1959]      Re-entry   vehicle,   using wooden   boxes   to   simulate   actual   components. Heavily   instrumented   for   re-entry   flight.   The black   “stripes”   around   the   nose   cone’s   outside perimeter are telemetry antennas.
#05.   [62938:   8/12/1959]      Re-entry   vehicle,   using wooden   boxes   to   simulate   actual   components. Heavily    instrumented    for    re-entry    flight.    To the   right   of   the   re-entry   vehicle   is   an   Engine Thrust Chamber.
AFT The   following   18   photographs   are   of   Jupiter   Missile   R&D   Aft Units    built    by    CCMD    in    1958    and    1959.    The    Aft    Unit    was mounted   away   from   and   on   top   of   the   Thrust   Unit.   The   Thrust Unit    consisted    of    propellant    tanks    and    the    [Rocketdyne] rocket   engine.   The   Aft   Unit   provided   vernier   adjustments   for flight   trajectory.   Contained   within   the   conical   Aft   Unit   was   the inertial    guidance    and    control    (G&C)    instrumentation    that provided    guidance    from    launch    to    Nose    Cone    designated target.      Attached   to   the   front   end   of   the   Aft   Unit   was   the   Nose Cone.    The    Aft    Unit    and    Nose    Cone    together    are    called    the Body Unit. Photo   73697   is   a   view   looking   into   the   front   of   an   Aft   Unit sitting   on   a   factory   work   stand.   On   the   right   in   the   photo marked   Army   is   the   Thrust   Unit   of   a   Redstone   Missile   also built     by     CCMD.     For     orientation,     the     four     compartments formed   by   the   X   crossed   instrument   panels   will   be   referred   to as   quadrants   with   number   one   at   the   top   and   clockwise   to quadrant number four. The    ST-90    stable    platform    was    mounted    in    quadrant    one floating   in   a   stable   position   with   respect   to   the   earth.   With   a system    of    gyroscopes    and    accelerometers    the    ST-90    would measure    deviations    in    three-dimensional    space    from    the missile’s    programed    flight    path,    then    provide    this    data    to other   instruments   which   created   and   provided   corrections   to maintain the Nose Cone on its programed course to target. The   word   CAUTION   is   marked   on   the   aft   bulkhead   which   with the   Nose   Cone   attached   to   the   front   of   the   Aft   Unit   sealed   the instrument compartment to atmospheric pressure. A   small   500   pound   thrust   rocket   located   in   the   rear   of   the   Aft Unit   would   be   fired   to   move   the   Aft   Unit   away   from   the   Thrust Unit   to   prevent   its   forward   momentum   from   colliding   with   the Body     Unit     after     Thrust     Unit     separation.     Upon     attaining ballistic   flight   path’s   apogee   the   Body   Unit   would   be   oriented in the same attitude in which it had left the atmosphere. Spatial    attitude    control    high    pressure    jets    in    the    Aft    Unit would   be   fired   causing   the   Body   Unit   to   tilt   so   that   the   Nose Cone   would   be   pointed   down   toward   the   earth,   at   which   time the   Aft   Unit’s   Spin   Rockets   would   be   fired   adding   Nose   Cone ballistic   stability   during   the   remainder   of   its   flight   to   target. The   Nose   Cone   would   then   be   separated   from   the   Aft   Unit   by detonating   primer   cord   wrapped   around   the   bolts   attaching the   Nose   Cone   to   the   Aft   unit.   The   Instrument   Compartment’s atmospheric   pressure   would   push   the   two   units   apart   thus ensuring the Aft Unit would not interfere with the Nose Cone. Pitot    Tubes,    extended    during    countdown,    were    mounted    in the   four   cylindrical   items   at   the   outer   skin   of   each   quadrant thus   providing   four   independent   airspeed   data   streams   to   the Guidance and Control package. (see Photo 73697). Ed     was     working     in     CCMD’s     Department     7262,     “Electro- Mechanical   Design,”   during   the   years   1958-1959   when   many   of these photos were taken.
[73697: 3/3/1960]  Looking into top of Guidance Package, the Aft Unit (was mounted to main body, on top of fuel tanks), located just behind the warhead. Explosive bolts would separate re-entry vehicle. Right is shown a Redstone Missile (Tactical Missile). [73697: 3/3/1960]  Looking into top of Guidance Package, the Aft Unit (was mounted to main body, on top of fuel tanks), located just behind the warhead. Explosive bolts would separate re-entry vehicle. Right is shown a Redstone Missile (Tactical Missile). [73697: 3/3/1960]  Looking into top of Guidance Package, the Aft Unit (was mounted to main body, on top of fuel tanks), located just behind the warhead. Explosive bolts would separate re-entry vehicle. Right is shown a Redstone Missile (Tactical Missile).
#06    [73697:    3/3/1960]        Looking    into    top    of Guidance   Package,   the   Aft   Unit   (was   mounted to   main   body,   on   top   of   fuel   tanks),   located just     behind     the     warhead.     Explosive     bolts would     separate     re-entry     vehicle.     Right     is shown a Redstone Missile (Tactical Missile).
[69864: 12/7/1959]  Looking into another quadrant, empty. Instrument compartment was in an "X" configuration.  [CCMD, Ed May] [69864: 12/7/1959]  Looking into another quadrant, empty. Instrument compartment was in an "X" configuration.  [CCMD, Ed May] [69864: 12/7/1959]  Looking into another quadrant, empty. Instrument compartment was in an "X" configuration.  [CCMD, Ed May]
#07.    [69864:    12/7/1959]        View    looking    into quadrant   1   during   an   early   stage   of   assembly. The    Aft    Unit    had    hatch    openings    in    each quadrant   to   provide   excess   for   the   installation of   the   instrumentation   and   were   covered   with hatch   panels   at   final   assembly.   In   the   field   the hatches    could    be    opened    for    any    necessary repairs
[69865: 12/7/1959]  Looking into another quadrant. The "ball joint" device is an attachment point for the ST-90 Stabilization Platform. Sheet metal cover over the exposed vertical bracket used for cooling around stabilization platform.  [CCMD, Ed May] [69865: 12/7/1959]  Looking into another quadrant. The "ball joint" device is an attachment point for the ST-90 Stabilization Platform. Sheet metal cover over the exposed vertical bracket used for cooling around stabilization platform.  [CCMD, Ed May] [69865: 12/7/1959]  Looking into another quadrant. The "ball joint" device is an attachment point for the ST-90 Stabilization Platform. Sheet metal cover over the exposed vertical bracket used for cooling around stabilization platform.  [CCMD, Ed May]
#08.    [69865:    12/7/1959]        Looking    also    into quadrant   1.   The   "ball   joint"   in   the   lower   left corner    is    an    attachment    point    for    the    ST-90 Stabilization      Platform.      The      sheet      metal structure   with   the   row   of   attaching   points   is the    mounting    surface    for    the    cover    placed over    the    ST-90    to    reduce    the    volume    to    be cooled.
[69866: 12/7/1959]  Looing into quadrant where the SD-90 was mounted. Can see the cover. SD-90 is the inertial guidance stabilization platform. [CCMD, Ed May] [69866: 12/7/1959]  Looing into quadrant where the SD-90 was mounted. Can see the cover. SD-90 is the inertial guidance stabilization platform. [CCMD, Ed May] [69866: 12/7/1959]  Looing into quadrant where the SD-90 was mounted. Can see the cover. SD-90 is the inertial guidance stabilization platform. [CCMD, Ed May]
#09:   [69866:   12/7/1959]      Close   up   view   of   the ST-90 " ball joint" attachment.
[69867: 12/7/1959]  Looking to SD-90 Quadrant. EO=Engineering Order.  [CCMD, Ed May] [69867: 12/7/1959]  Looking to SD-90 Quadrant. EO=Engineering Order.  [CCMD, Ed May] [69867: 12/7/1959]  Looking to SD-90 Quadrant. EO=Engineering Order.  [CCMD, Ed May]
#10:    [69867:    12/7/1959]        In    quadrant    1    the white    marking    on    the    black    ST-90    mounting ring    are    to    indicate    the    latest    engineering change order (EO) incorporated into the part.
[70239: 12/10/1959]  Showing Stable Platform Mounting Bracket, full yoke. Cooling fan blowers at top and bottom.  [CCMD, Ed May] [70239: 12/10/1959]  Showing Stable Platform Mounting Bracket, full yoke. Cooling fan blowers at top and bottom.  [CCMD, Ed May] [70239: 12/10/1959]  Showing Stable Platform Mounting Bracket, full yoke. Cooling fan blowers at top and bottom.  [CCMD, Ed May]
#11.   [70239:   12/10/1959]      Looking   straight   into quadrant   1.   The   squared   shaped   structure   is the   mounting   ring   for   the   ST-90.   At   the   bottom of   the   V   is   the   300   CFM   blower   and   vents   to circulate cool air over the ST-90 during flight.
[70240: 12/10/1959]  Showing Stable Platform Mounting Bracket, full yoke. Cooling fan blowers at bottom and inside. R/S Electrical Connectors covered during assembly to keep out dirt.  [CCMD, Ed May] [70240: 12/10/1959]  Showing Stable Platform Mounting Bracket, full yoke. Cooling fan blowers at bottom and inside. R/S Electrical Connectors covered during assembly to keep out dirt.  [CCMD, Ed May] [70240: 12/10/1959]  Showing Stable Platform Mounting Bracket, full yoke. Cooling fan blowers at bottom and inside. R/S Electrical Connectors covered during assembly to keep out dirt.  [CCMD, Ed May]
#12.     [70240:     12/10/1959]          Showing     Stable Platform   Mounting   Bracket,   full   yoke.   Cooling fan     blowers     at     bottom     and     inside.     R/S Electrical   Connectors   covered   during   assembly to keep out dirt.
#13.    [69862:    12/7/1959]        View    looking    at    the right-side   instrument   panel   of   quadrant   2.   R&D missiles    used    plywood    instrument    panel    but for    weight    reduction    production    units    used honeycombed   aluminum.   The   large   tank   held in   place   with   the   two   metal   straps   is   the   Ln2 (liquid     nitrogen)     container     for     the     in-flight cooling   system.   It   is   wrapped   with   insulation held   in   place   with   duct   tape.   The   corrugated   tubing   at the    right    side    is    for    the    exterior    pre-fight    cooling system.
[69862: 12/7/1959]  Aft Unit Instrumentation, using honeycombed Aluminum mounting surfaces. Liquid Nitrogen in-flight cooling tank. Wrapped with insulation, wrapped with duct tape to hold in place.  [CCMD, Ed May] [69862: 12/7/1959]  Aft Unit Instrumentation, using honeycombed Aluminum mounting surfaces. Liquid Nitrogen in-flight cooling tank. Wrapped with insulation, wrapped with duct tape to hold in place.  [CCMD, Ed May
#14.   [69863:   12/7/1959]      View   looking   at   the   left side   instrument   panel   of   quadrant   2.   Aft   Unit Instrumentation,           using           honeycombed Aluminum   mounting   surfaces.   Liquid   Nitrogen in-flight        cooling        tank.        Wrapped        with insulation,   wrapped   with   duct   tape   to   hold   in place.
[69863: 12/7/1959]  Aft Unit Instrumentation, using honeycombed Aluminum mounting surfaces. Liquid Nitrogen in-flight cooling tank. Wrapped with insulation, wrapped with duct tape to hold in place.  [CCMD, Ed May] [69863: 12/7/1959]  Aft Unit Instrumentation, using honeycombed Aluminum mounting surfaces. Liquid Nitrogen in-flight cooling tank. Wrapped with insulation, wrapped with duct tape to hold in place.  [CCMD, Ed May] [69863: 12/7/1959]  Aft Unit Instrumentation, using honeycombed Aluminum mounting surfaces. Liquid Nitrogen in-flight cooling tank. Wrapped with insulation, wrapped with duct tape to hold in place.  [CCMD, Ed May] [73698: 3/3/1960]  Top of Liquid Nitrogen Cooling Tank, showing flex tubing that routes cool air to G&C package. Aluminum tubing was high pressure air feeding tank to circulate nitro for cooling.  [CCMD, Ed May] [73698: 3/3/1960]  Top of Liquid Nitrogen Cooling Tank, showing flex tubing that routes cool air to G&C package. Aluminum tubing was high pressure air feeding tank to circulate nitro for cooling.  [CCMD, Ed May] [73698: 3/3/1960]  Top of Liquid Nitrogen Cooling Tank, showing flex tubing that routes cool air to G&C package. Aluminum tubing was high pressure air feeding tank to circulate nitro for cooling.  [CCMD, Ed May]
#15.   [73698:   3/3/1960]      View   looking   at   the   top of   the   Ln2   tank.   The   three   corrugated   tubes are   for   routing   cooled   air   from   the   tank   into other   quadrants.   The   Ln2   is   pumped   into   the tank    during    countdown    through    the    small tube elbowed down into the tank. 
[69868: 12/7/1959]  Black box is a 400cps Inverter, converted 28vdc DC to 400Hz AC. Unit 300cf/s cooling source was taped off.  [CCMD, Ed May] [69868: 12/7/1959]  Black box is a 400cps Inverter, converted 28vdc DC to 400Hz AC. Unit 300cf/s cooling source was taped off.  [CCMD, Ed May] [69868: 12/7/1959]  Black box is a 400cps Inverter, converted 28vdc DC to 400Hz AC. Unit 300cf/s cooling source was taped off.  [CCMD, Ed May]
#16.    [69868:    12/7/1959]        View    looking    into quadrant   3   under   the   black   instrument   (which is   an   inverter   for   converting   28-volt   DC   into 400Hz    AC)    is    the    blower    for    the    preflight cooling system.
[69869: 12/7/1959]  Looking into another quadrant; shows honeycomb aluminum mounting panel. Part of guidance, "Program Device," made by Ford.  [CCMD, Ed May] [69869: 12/7/1959]  Looking into another quadrant; shows honeycomb aluminum mounting panel. Part of guidance, "Program Device," made by Ford.  [CCMD, Ed May] [69869: 12/7/1959]  Looking into another quadrant; shows honeycomb aluminum mounting panel. Part of guidance, "Program Device," made by Ford.  [CCMD, Ed May]
#18:   [69869:   12/7/1959]      The   Flight   Programmer is    mounted    on    the    left    instrument    panel    of quadrant   4.   The   Ln2   fill   tube   passes   thru   the panel   across   the   top   of   quadrant   1   thru   the right    panel    of    quadrant    2    and    into    the    Ln2 tank.   At   the   top   of   the   photo   is   the   extendible pitot tube canister.  
#19.   [33824:   11/03/58]   The   rear   end   of   an   Aft Unit   sitting   on   a   factory   work   stand.   At   the   left is   one   of   the   fiber   glass   spheres   that   held   the high-pressure     air     for     the     spatial     attitude control system.
[33824: 11/03/58] Looking at the bottom of the G&C package. Sphere is fiberglass for high pressure air, tested to 7500psi, Flight Tested to 3,000 psi. Spatial Directional Countrol.  [CCMD, Ed May] [33824: 11/03/58] Looking at the bottom of the G&C package. Sphere is fiberglass for high pressure air, tested to 7500psi, Flight Tested to 3,000 psi. Spatial Directional Countrol.  [CCMD, Ed May] [33824: 11/03/58] Looking at the bottom of the G&C package. Sphere is fiberglass for high pressure air, tested to 7500psi, Flight Tested to 3,000 psi. Spatial Directional Countrol.  [CCMD, Ed May] [69870: 12/7/1959]  Looking into 4th quadrant, tubing covered with tape was part of cooling system.  [CCMD, Ed May] [69870: 12/7/1959]  Looking into 4th quadrant, tubing covered with tape was part of cooling system.  [CCMD, Ed May] [69870: 12/7/1959]  Looking into 4th quadrant, tubing covered with tape was part of cooling system.  [CCMD, Ed May]
#17.    [69870:    12/7/1959]        View    looking    into quadrant   4.   The   duck   tapped   tubing   is   the   line for filling the Ln2 tank during countdown.
#22   [21108:   5/5/58]   Very   early   mockup   looking into   quadrant   3   most   of   the   instruments   are wooden mockups of the real items.
[21108: 5/5/58] Early mockup, parts simulated with wooden parts. Some parts were real. Wires go to dummy connectors.  [CCMD, Ed May] [21108: 5/5/58] Early mockup, parts simulated with wooden parts. Some parts were real. Wires go to dummy connectors.  [CCMD, Ed May] [21108: 5/5/58] Early mockup, parts simulated with wooden parts. Some parts were real. Wires go to dummy connectors.  [CCMD, Ed May] [33816: 11/03/58] Instrument panels are made out of plywood. Developed honeycomb aluminum, R&D Warhead early in program. Two cutouts show 2ea antennas telemetry.  [CCMD, Ed May] [33816: 11/03/58] Instrument panels are made out of plywood. Developed honeycomb aluminum, R&D Warhead early in program. Two cutouts show 2ea antennas telemetry.  [CCMD, Ed May] [33816: 11/03/58] Instrument panels are made out of plywood. Developed honeycomb aluminum, R&D Warhead early in program. Two cutouts show 2ea antennas telemetry.  [CCMD, Ed May]
#21.     [33816:     11/03/58]     View     looking     into quadrant   4   of   a   very   early   R&D   Aft   Unit.   Note that    the    instrumental    panels    are    plywood. Developed       honeycomb       aluminum,       R&D Warhead   early   in   program.   Two   cutouts   show 2ea antennas telemetry.
#20: [33826: 11/03/58]  #19: [33824: (11/3/1958)] Thrust Unit electric cables would be connected to the five connectors shown for the transmission of signals such as rocket engine gimbling instructions for directional control, burn time and Thrust Unit separation command. At this point of assembly, the 500 pound Vernier rocket motor is not yet installed. [33826: 11/03/58]  Another view of the G&C package. Six electrical connectors feed propulsion unit (fuel tanks, engine).  [CCMD, Ed May] [33826: 11/03/58]  Another view of the G&C package. Six electrical connectors feed propulsion unit (fuel tanks, engine).  [CCMD, Ed May] [33826: 11/03/58]  Another view of the G&C package. Six electrical connectors feed propulsion unit (fuel tanks, engine).  [CCMD, Ed May]

GROUND CONTROL EQUIPMENT

The   human   interface   to   the   Jupiter   missile   came   through   the Launch    Consoles    contained    within    the    Launch    Trailers.    The following    five    photos    show    the    Launch    Trailer    and    their console’s initial configuration.
[71890: 1/28/1960]  Launch Control Trailer Schematic.  [CCMD, Ed May] [71890: 1/28/1960]  Launch Control Trailer Schematic.  [CCMD, Ed May] [71890: 1/28/1960]  Launch Control Trailer Schematic.  [CCMD, Ed May]
#23.    [71890:    1/28/1960]        Floor    plan    of    the Electrical   Equipment   Trailer   which   was   used to     run     periodic     checkups     of     all     missile instrumentation.
[47148: 05/06/1959]  Inside Launch Trailer.  [CCMD, Ed May] [47148: 05/06/1959]  Inside Launch Trailer.  [CCMD, Ed May] [47148: 05/06/1959]  Inside Launch Trailer.  [CCMD, Ed May]
#24.    [47148:    05/06/1959]        View    looking    aft    in the Launch Control Trailer.
[44647: 04/02/1959]  Inside Launch Trailer. Launch Console was forward in trailer.  [CCMD, Ed May] [44647: 04/02/1959]  Inside Launch Trailer. Launch Console was forward in trailer.  [CCMD, Ed May] [44647: 04/02/1959]  Inside Launch Trailer. Launch Console was forward in trailer.  [CCMD, Ed May]
#25.   [44647:   04/02/1959]      Also   looking   aft   in the Launch Control Trailer.
[47147: 05/06/1959]  Launch Console for 3 missiles. One display for each of the 3 site missiles.  [CCMD, Ed May] [47147: 05/06/1959]  Launch Console for 3 missiles. One display for each of the 3 site missiles.  [CCMD, Ed May] [47147: 05/06/1959]  Launch Console for 3 missiles. One display for each of the 3 site missiles.  [CCMD, Ed May]
#27.   [47147:   05/06/1959]      Close   up   view   of   the Launch Control Console.
[29998: 9/22/58] Launch Console for 3 missiles. One display for each of the 3 site missiles. [CCMD, Ed May] [29998: 9/22/58] Launch Console for 3 missiles. One display for each of the 3 site missiles. [CCMD, Ed May] [29998: 9/22/58] Launch Console for 3 missiles. One display for each of the 3 site missiles. [CCMD, Ed May]
#26.       [29998:       9/22/58]       Launch       Control Console,    one    panel    for    each    of    the    three missiles on the launch site.
Jupiter’s Ground Equipment [49597, 6/18/1959] Chrysler R&D Missile; CM AP initials:  C= Chrysler  M=Missile  AP?=21  = Chrysler Missile 21.  [CCMD, Ed May] [49597, 6/18/1959] Chrysler R&D Missile; CM AP initials:  C= Chrysler  M=Missile  AP?=21  = Chrysler Missile 21.  [CCMD, Ed May] [49597, 6/18/1959] Chrysler R&D Missile; CM AP initials:  C= Chrysler  M=Missile  AP?=21  = Chrysler Missile 21.  [CCMD, Ed May]
#28.   [49597;   6/18/1959]   Chrysler   R&D   Missile; CM     AP     initials:          C=     Chrysler          M=Missile       AP?=21      =   Chrysler   Missile   21   [for   reasons   of security     to     conceal     the     number     of     the missile   a   word   was   used   maybe   in   this   case Able B for 2 and A for 1.]
[43361: 03/10/1959]  Juno Missile, moon shot or placing object in orbit? Cooling tower falling away on right side.  [CCMD, Ed May] [43361: 03/10/1959]  Juno Missile, moon shot or placing object in orbit? Cooling tower falling away on right side.  [CCMD, Ed May] [43361: 03/10/1959]  Juno Missile, moon shot or placing object in orbit? Cooling tower falling away on right side.  [CCMD, Ed May]
#29.   [43361:   03/10/1959]      Juno   Missile,   moon shot   or   placing   object   in   orbit?   Cooling   tower falling away on right side.
Last Updated:  01/21/2018 16:36