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[Music]

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this is the first quarterly coal report

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on the Saturn C 5 designated by the

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National Aeronautics and Space

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Administration as the vehicle which will

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launch the Apollo spacecraft to

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accomplish circumlunar flight and manned

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lunar landings the Saturn C 5 booster or

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first stage identified as the s 1 C is

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now under joint development by the

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George C Marshall Space Flight Center

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and the Boeing Company it will have five

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f-1 engines producing the total thrust

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of seven and a half million pounds

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Rocketdyne division of North American

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the second stage s2 is under development

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by the space systems and information

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division of North American Aviation it's

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five G two engines using liquid hydrogen

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will generate 1 million pounds of thrust

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Rocketdyne is also contractor for the j2

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the third stage known as s4b

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is being developed by Douglas Aircraft

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Company it will use a single-engine j2

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designed to carry three men the Apollo

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spacecraft will ride atop the third

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stage to complete the Saturn C 5 space

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vehicle this report will highlight major

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facilities build-up activity for

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manufacture and testing of s1 c s2 and

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s4 b stages at the Marshall Space Flight

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Center where overall direction of the

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Saturn program emanates and where ground

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test s 1c stages will be assembled and

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tested some plant facilities are now

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being rapidly reoriented from the c1 to

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the c5 program for example entrances to

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the fabrication and assembly buildings

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had to be considerably enlarged to allow

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movement of the vehicle a new components

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transporter is being assembled at

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Marshall for use in moving various s1c

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parts such as bulkheads and tank

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sections from one area to another 32

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feet tall the transporter will carry its

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loads suspended from hooks on cables at

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each side adjacent to the fabrication

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area at Marshalls manufacturing

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engineering division construction has

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begun on an s-1 C combination vertical

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assembly station and hydrostatic test

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our the 160 foot tall structure will

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also be used for cleaning of finished

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tanks located near the present Saturn C

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1 dynamic test and will be a 360 foot

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high C 5 dynamic stand for which design

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work has been completed a dynamic test

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vehicle assembled at Marshall who will

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be suspended in the tower and vibrated

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to determine simulated in flight

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responses work is progressing on

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construction of the static test stand to

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be used for captive firing s1c stages

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work on the test and foundation and

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Control Centre has been underway for

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and a contract has been awarded for

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construction of the tower itself which

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will measure 160 feet square at the base

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and stand 405 feet high a contract for

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excavation and other preliminary work on

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Marshalls single f1 engine static test

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and has also been awarded and test and

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design has been completed the stand will

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be approximately 200 feet high to

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full-scale fiberglass mock-ups of s1c

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locks and fuel tank bulkheads have been

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received by the Marshall Center from

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Boeing company's plant at Wichita Kansas

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they will become part of the s 1c

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mock-up to be assembled at Marshall

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consisting of eight gore segments the

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bulkhead is 33 feet in diameter and 10

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feet high at the center bulkhead

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fabrication fixtures such as this device

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for cutting and welding gore fitting

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connections are now being installed at

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Marshall in preparation for fabrication

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work all the fixtures were provided by

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this Gore trim fixture trims the top

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edge of the base and the bottom edge of

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the apex of each Gore in order to make a

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joint to weld the two pieces together

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portable vacuum chucks or holding

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devices keep the Gore's in place while

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they're being trimmed and welded they

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send apex portions are joined on this

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Gore welding fixture it's welding

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platform is mounted over a pit and can

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be tilted 30 degrees making it possible

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to weld uphill at all times

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welding downward is undesirable because

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the weld will run off instead of

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puddling as is necessary to form a

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strong weld this meridian edge Gore trim

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fixture is used for trimming the Gore's

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lengthwise a large vacuum chuck from

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which air is evacuated by a pump holds

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the gore during trimming Gore's are then

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placed in this bulkhead assembly welding

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station where meridian wells are

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performed to join them together the

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process is repeated eight times to make

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a bulkhead assembly after each core is

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welded the turntable welding platform is

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rotated 45 degrees to position the next

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Gore for the weld head which remains in

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place this fixture is used to trim each

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bulkhead assembly to a 54 inch diameter

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opening at the top and then weld in the

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bulkhead closure piece to complete the

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bulkhead fabrication process at Wichita

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Boeing's 80-acre plant to area is the

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site of the company's program for Saturn

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c5 support tooling and fabrication work

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preliminary milling on c5 booster test

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panels was accomplished on these tape

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controls Kim Mills with working length

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and width of 90 feet and 12 feet

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respectively the same skinned mills will

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be used for pocket milling required on

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the tank and gorse

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segment and also for milling integrally

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stiffened tank skins fiberglass molds or

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layups are being formed here for the

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tank end Gore segment bulge form dies

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eight such segments will form the ends

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for fuel and blocks tanks for c5

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boosters the master form for the segment

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is fabricated of plaster others Saturn

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layups

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are made of fiberglass one such

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fiberglass mold is this base core

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segment welding on all tools to be used

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in Boeing's fabrication of parts for the

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Saturn c5 program is performed in the

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Boeing Wichita weld shop this section

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represents the framework for the base

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portion of the Bulge formed i-4 tank end

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Gore's wire feed welding equipment and

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other advanced fabrication techniques

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are employed in all areas of Saturn work

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at the Wichita facility at Marshall

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centers masuo operations in New Orleans

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the huge plant is being readied for

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when NASA occupied the former Army

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Ordnance plant its overhead

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superstructure used in manufacture of

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tank engines during World War two was

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too low for Saturn booster assembly

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plant renovation performed under

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contract by Mason rust company of New

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Orleans consisted largely of removal of

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the surplus overhead grillage such as

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rails cranes and heat ducts their

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removal now allows an overhead clearance

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of 40 feet which will provide 6 inches

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of clearance for the booster in the

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approximately 2,000 tons of steel were

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cut out of the overhead superstructure

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and hauled from the plant to be sold as

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scrap a 50-foot diameter hole had to be

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broken in the floor in preparation for a

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specially constructed foundation for

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Boeing's Massey

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100-ton boring mil a wooden retaining

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wall with steel spider reinforcement

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kept the sides of the 15-foot deep

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excavation from caving in the old piling

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on which the original floor was mounted

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was cut off at the bottom of the hole

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and augmented by an additional 116 new

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files which were driven 30 feet into the

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ground a concrete cap was then poured on

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the files and the foundation built up

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with concrete and reinforced steel the

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boring mill was shipped to masu on eight

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flat cars from the Army's Detroit

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steam cleaning of the mill was

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accomplished after its delivery to the

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mature plant emplacement of the mill on

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its foundation required extreme care to

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ensure proper meshing of gear systems

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the turntable weighing over 70 tons was

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not large enough for Saturn's needs so

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extensions were manufactured to increase

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the diameter by approximately twelve

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feet at Ingalls shipyard in Pascagoula

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Mississippi rolling of aluminum ingots

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for wiring segments of s1c stages was

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recently performed for Boeing why Rings

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will be used to connect bulkheads to

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fuel and blocks tank skins in order to

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check for cracks dye penetrant tests

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were performed on ingots before during

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and after the rolling operation ingots

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measured 5 inches thick and 34 feet long

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the desired final radius of 16 and a

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half feet was obtained by rolling a

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little at a time and checking it by hand

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with a plywood template during rolling

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smooth metal collars were placed on the

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heavy hydraulically operated rollers to

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a test ingot after its normal rolling

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operation had been accomplished was

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replaced in the rollers and then rolled

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beyond 360 degrees in a checkout attempt

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to break the ingot even at this extreme

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over bend however no breaks occurred the

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ends of normally rolled segments were

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machined at the shipyard to an

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approximate V point when the three

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segments which formed the wiring are

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placed together for welding the points

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of the V's touch and the open V's formed

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both inside and outside the ring surface

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are filled with metal to form strong

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heavy welds from the center out in an

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interim weld facility set up at masu

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welders were trained to operate the

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automatic machines used to make the Wai

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ring Wells sonic and x-ray testing of

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Wells was conducted to discover any

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flaws or cracks the first actual wiring

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weld was performed in Boeing's

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production weld facility in December

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using personnel and equipment formerly

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the boring mill at masu was put to its

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initial use in a test operation to

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machine the first wiring segments to

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finish dimensions one segment was cut

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into small sections for test pieces

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which will be used for experimental

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welding to determine if the wiring can

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be welded after it is machined rather

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than before following the tests the

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three segments will be welded together

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to determine the feasibility of welding

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construction of the foundation for the

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new vertical Assembly Building at massú

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is now well underway the building will

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have three tank assembly areas one

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chemical tank test area and one stage

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vertical assembly area at Rocketdyne

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where Saturn's f1 engines are being

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developed inspection of the engines

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modified sixteen to one thrust chamber

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extension skirt after its first short

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duration firing showed that collapsing

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and longitudinal buckling have been

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eliminated in this design a new exhaust

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manifold now being employed on the f1 is

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smaller and more circular in shape than

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the previous design this configuration

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is intended to reduce the axial loading

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on the skirt support flange which

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results in membrane stresses in the

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manifold shell rocket dines new model

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one LOX pump has been undergoing tests

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at Santa Susana in this test setup a

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pipe is connected to the top of the pump

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permitting testing with a direct flow

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pump performance is then compared with

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performance when the pump is flowed

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through the normal inlets in the elbows

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the f1 heat exchanger designed to

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provide pressurization for the LOX and

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fuel tanks has been tested a number of

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times at components test lab number

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00:15:28,890 --> 00:15:26,320
three several injector designs such as

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00:15:30,600 --> 00:15:28,900
this LOX dispersion injector have been

281
00:15:34,620 --> 00:15:30,610
tested in an effort to increase

282
00:15:36,990 --> 00:15:34,630
combustion stability margins other

283
00:15:40,500 --> 00:15:37,000
designs tested include the baffled

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00:15:44,340 --> 00:15:40,510
divergent ring injector low fuel Delta P

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00:15:49,680 --> 00:15:44,350
injector 21 compartment baffled injector

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00:15:52,320 --> 00:15:49,690
and the divergent ring injector as part

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00:15:53,820 --> 00:15:52,330
of the LOX dome oscillation study tests

288
00:15:56,160 --> 00:15:53,830
have been conducted on rocket dean's

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00:15:58,770 --> 00:15:56,170
high flow test bench at varying

290
00:16:02,340 --> 00:15:58,780
pressures this data will be evaluated

291
00:16:05,070 --> 00:16:02,350
and compared with data from hot testing

292
00:16:07,320 --> 00:16:05,080
a full-scale f1 engine mock-up has been

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00:16:09,390 --> 00:16:07,330
delivered by Rocketdyne to the Marshall

294
00:16:12,240 --> 00:16:09,400
Center where it was mounted vertically

295
00:16:14,580 --> 00:16:12,250
for tests and a gimbal expand later

296
00:16:23,070 --> 00:16:14,590
it'll be mounted in a partial mock-up of

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00:16:25,320 --> 00:16:23,080
the s1 see thrust structure final

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00:16:26,940 --> 00:16:25,330
assembly of saturn s2 stages will be

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00:16:29,670 --> 00:16:26,950
accomplished at the new Seal Beach

300
00:16:32,300 --> 00:16:29,680
California facility of North Americans

301
00:16:35,580 --> 00:16:32,310
space and Information Systems Division

302
00:16:37,620 --> 00:16:35,590
construction began in August s and I D

303
00:16:39,750 --> 00:16:37,630
personnel occupied a portion of the

304
00:16:41,910 --> 00:16:39,760
facility's bulkhead fabrication building

305
00:16:46,710 --> 00:16:41,920
in December to coordinate tooling

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00:16:48,210 --> 00:16:46,720
installation this one 248 scale model of

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00:16:50,250 --> 00:16:48,220
the seal Beach vertical assembly

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00:16:53,970 --> 00:16:50,260
facility is being used to evaluate

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00:16:56,100 --> 00:16:53,980
proposed s2 assembly sequences and to

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00:16:58,710 --> 00:16:56,110
check integration of tools facilities

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00:17:03,270 --> 00:16:58,720
material handling devices and booster

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00:17:05,460 --> 00:17:03,280
components production tooling for use at

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00:17:08,580 --> 00:17:05,470
seal Beach an assembly and welding of s2

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00:17:11,460 --> 00:17:08,590
bulkheads is now being fabricated at s

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00:17:16,010 --> 00:17:11,470
and IDs Downey plant delivery of weld

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00:17:20,670 --> 00:17:18,450
construction of s and ID's el Toro

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00:17:23,040 --> 00:17:20,680
facility for high energy forming of

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00:17:25,410 --> 00:17:23,050
bulkhead gora segments and high energy

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00:17:29,280 --> 00:17:25,420
sizing of bulkheads has been virtually

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00:17:31,290 --> 00:17:29,290
completed a master mold for bulkhead

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00:17:34,170 --> 00:17:31,300
gore segment tooling has been used at

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00:17:36,840 --> 00:17:34,180
Downey to form a master facility tool an

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00:17:39,120 --> 00:17:36,850
over pressed template and soft tooling

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00:17:43,710 --> 00:17:39,130
for the high energy forming program at

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00:17:46,110 --> 00:17:43,720
El Toro high energy forming dyes are

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00:17:49,560 --> 00:17:46,120
being machined from rough formed steel

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00:17:51,930 --> 00:17:49,570
using scape machining techniques these

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00:17:54,480 --> 00:17:51,940
dies due to their size shape and weight

329
00:17:57,270 --> 00:17:54,490
could not be machined by conventional

330
00:17:58,920 --> 00:17:57,280
methods in February the forming dyes

331
00:18:04,850 --> 00:17:58,930
will be delivered to the El Toro

332
00:18:09,660 --> 00:18:07,320
another major construction activity

333
00:18:12,210 --> 00:18:09,670
under way for the s2 program is

334
00:18:15,850 --> 00:18:12,220
preparation for a new static test end

335
00:18:17,950 --> 00:18:15,860
called cooker for at Santa Susana

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00:18:25,779 --> 00:18:17,960
the coca one test and is also being

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00:18:27,630 --> 00:18:25,789
modified for s2 1/4 scale s2 test tank

338
00:18:30,370 --> 00:18:27,640
has recently been fabricated and

339
00:18:32,230 --> 00:18:30,380
hydrostatically tested at Downey to

340
00:18:36,909 --> 00:18:32,240
prove the design integrity of the

341
00:18:39,070 --> 00:18:36,919
insulation system 1/4 scale working

342
00:18:42,220 --> 00:18:39,080
model of one of the 3 umbilical arms

343
00:18:47,620 --> 00:18:42,230
required to service the s2 stage has

344
00:18:50,259 --> 00:18:47,630
also been completed Cornell aeronautical

345
00:18:52,840 --> 00:18:50,269
laboratory in Buffalo New York has

346
00:18:56,080 --> 00:18:52,850
concluded a series of tests for s and ID

347
00:18:58,090 --> 00:18:56,090
to determine the s2 s base environment

348
00:19:00,700 --> 00:18:58,100
in terms of temperature heating rates

349
00:19:02,529 --> 00:19:00,710
and pressure distribution and to

350
00:19:05,649 --> 00:19:02,539
establish the optimum deflector and

351
00:19:09,159 --> 00:19:05,659
shrouding arrangement for the stages 5j

352
00:19:10,779 --> 00:19:09,169
two engines using a 125th scale model

353
00:19:12,909 --> 00:19:10,789
tests were conducted at a pressure

354
00:19:18,370 --> 00:19:12,919
equivalent to an altitude of 240

355
00:19:20,320 --> 00:19:18,380
thousand feet at Douglas Aircraft

356
00:19:22,779 --> 00:19:20,330
Company where design development

357
00:19:25,870 --> 00:19:22,789
fabrication and testing of the Saturn C

358
00:19:28,690 --> 00:19:25,880
fives third stage s 4 B will be

359
00:19:30,820 --> 00:19:28,700
accomplished structural layout drawings

360
00:19:34,090 --> 00:19:30,830
being prepared by Douglas are nearing

361
00:19:37,330 --> 00:19:34,100
completion and work is underway on

362
00:19:39,669 --> 00:19:37,340
detailed stage structural drawings at

363
00:19:42,340 --> 00:19:39,679
Douglas Sacramento test area where

364
00:19:46,060 --> 00:19:42,350
static tests of the Saturn C one's s4

365
00:19:48,669 --> 00:19:46,070
stage are conducted a new facility for

366
00:19:51,279 --> 00:19:48,679
ground testing of the larger s4 B stage

367
00:19:55,299 --> 00:19:51,289
is being planned the complex will

368
00:19:57,669 --> 00:19:55,309
include static test stands a blockhouse

369
00:20:01,450 --> 00:19:57,679
propellant and high-pressure gas systems

370
00:20:04,060 --> 00:20:01,460
and supporting utilities at Rocketdyne

371
00:20:06,639 --> 00:20:04,070
Santa Susana area buildup of test

372
00:20:11,289 --> 00:20:06,649
facilities continues for the j2 engine

373
00:20:15,149 --> 00:20:11,299
common to s2 and s4 b stages vertical

374
00:20:18,549 --> 00:20:15,159
test and number two is almost complete

375
00:20:21,370 --> 00:20:18,559
at Delta test and number two which will

376
00:20:24,210 --> 00:20:21,380
be used for 500 second runs outside

377
00:20:26,919 --> 00:20:24,220
lakhs run tanks are in place and

378
00:20:28,840 --> 00:20:26,929
fabrication of the 90,000 gallon liquid

379
00:20:29,410 --> 00:20:28,850
hydrogen run vessel is virtually

380
00:20:35,740 --> 00:20:29,420
finished

381
00:20:38,950 --> 00:20:35,750
a hard mock-up of the block 3j2 engine

382
00:20:40,930 --> 00:20:38,960
has recently been completed oriented to

383
00:20:45,430 --> 00:20:40,940
vehicle requirements it represents the

384
00:20:46,180 --> 00:20:45,440
initial flight readiness engine since

385
00:20:48,670 --> 00:20:46,190
the j2 s

386
00:20:52,150 --> 00:20:48,680
first long-duration static test on

387
00:20:54,310 --> 00:20:52,160
October 4th 1962 in which the engine

388
00:20:57,100 --> 00:20:54,320
fired for more than four minutes at full

389
00:21:05,299 --> 00:20:57,110
thrust a number of similar tests have

390
00:21:11,820 --> 00:21:08,400
Saturn c5 vehicles will be launched from

391
00:21:13,650 --> 00:21:11,830
complex 39 in the new NASA area for

392
00:21:18,870 --> 00:21:13,660
which land has been acquired north of

393
00:21:21,480 --> 00:21:18,880
cape canaveral complex 39 covering

394
00:21:24,299 --> 00:21:21,490
30,000 acres and containing two or more

395
00:21:28,350 --> 00:21:24,309
launch pads will embody a new concept in

396
00:21:30,690 --> 00:21:28,360
launch facilities Saturn vehicles will

397
00:21:32,910 --> 00:21:30,700
be completely erected and checked out in

398
00:21:34,890 --> 00:21:32,920
a 48 story tall vertical Assembly

399
00:21:41,520 --> 00:21:34,900
Building about three miles from the

400
00:21:44,700 --> 00:21:41,530
launch site the building will contain

401
00:21:46,799 --> 00:21:44,710
four bays in each of which a Saturn can

402
00:21:49,350 --> 00:21:46,809
be erected mated to the Apollo

403
00:21:52,110 --> 00:21:49,360
spacecraft and check out on a launch

404
00:21:57,600 --> 00:21:52,120
rack which also supports its 400 foot

405
00:21:59,190 --> 00:21:57,610
umbilical Tower the launch ready Saturn

406
00:22:02,370 --> 00:21:59,200
will then be transported to the

407
00:22:08,070 --> 00:22:02,380
launching pad by means of a 2,500 tonne

408
00:22:10,410 --> 00:22:08,080
crawler vehicle at the pad the 20-foot

409
00:22:12,900 --> 00:22:10,420
high crawler will employ its hydraulic

410
00:22:25,960 --> 00:22:12,910
cylinders to lower the rack and vehicle

411
00:22:31,490 --> 00:22:29,060
launching of the Saturn c5 from Cape

412
00:22:34,009 --> 00:22:31,500
Canaveral will be a giant step in the

413
00:22:37,159 --> 00:22:34,019
lunar orbital rendezvous procedure which

414
00:22:42,790 --> 00:22:37,169
has been chosen by NASA as prime mission