Apollo and America's Moon Landing Program: History of the Development Program of the Saturn Rocket and the Saturn V from 1957 to 1968 by the Marshall Space Flight Center
National Aeronautics and Space Administration (NASA), World Spaceflight News, David S. Akens
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SATURN ILLUSTRATED CHRONOLOGY
by David S. Akens
George C. Marshall Space Flight Center * Historical Office * Management Services Office * MHR-5
Saturn's First Eleven Years * April 1957 through April 1968
January 20, 1971
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In April 1957 the scientific organization directed by Dr. Wernher von Braun began studies which led to Saturn, America's first rocket developed for space investigation. The team at Redstone Arsenal, Alabama, hoped to design launch vehicles that could carry 20,000- to 40,000-pound payloads for orbital missions or 6000 to 12,000-pound payloads for escape missions. High-thrust booster stages were essential.
In December 1957 the von Braun group, then working with the Army Ballistic Missile Agency (ABMA), proposed a program to the Department of Defense (DOD).1 At that time the United States was considering an integrated missile and space vehicle development program. Creation of a booster with 1,500,000 pounds of thrust was the aim of the proposed program.
To secure this much power ABMA first considered clustering four 380,000-pound thrust Rocketdyne E-1 engines.
This initial concept was discarded because of the time required to complete development of this type engine. However, ABMA continued studies to determine if engines already developed could be used.
On August 15, 1958, the Advanced Research Projects Agency (ARPA) formally initiated what was to become the Saturn project. The agency, a separately organized research and development arm of the Department of Defense, authorized ABMA to conduct a research and development program at Redstone Arsenal for a 1,500,000 pound thrust vehicle booster. A number of available rocket engines would be clustered. This design would be tested by a full-scale static firing by the end of 1959.2
The liquid oxygen (LOX) and fuel tanks developed for the Redstone and Jupiter missiles could be modified for use in the proposed booster. An existing engine, the S-3D, used on both the Thor and Jupiter missiles, could be modified to produce an increased thrust of 188,000 pounds. Numerous tools and fixtures developed for the Redstone and Jupiter program could also be used with comparatively little modification. Thus it was possible to begin booster development with hardware of proven reliability. Time for design and development of some important booster components and tooling could be significantly shortened and cost reduced.
As an immediate step a contract was awarded Rocketdyne Division of North American Aviation on September 11, 1958, to uprate S-3D, the Thor-Jupiter engine. After redesign, simplification, and modification, the engine would be the H-1.
In October 1958 ARPA expanded its program objectives. A multistage carrier vehicle capable of performing advanced space missions would be built. The vehicle was tentatively identified as Juno V. ARPA requested Redstone personnel to study a complete vehicle system so that upper-stage selection and development could begin, and initiated a study of Atlantic Missile Range (AMR) launch facilities which could accommodate the launch vehicle.3 Later, on December 11, 1958, ARPA authorized the Army Ordnance Missile Command (AOMC) to begin design, modification, and construction of a captive static test tower and facilities for use in the booster development program. AOMC was also to determine the design requirements for necessary launch facilities.4
While the booster-vehicle program was being formulated and expanded, development work on the H-1 engine continued. The first full-power H-1 engine firing occurred in December 1958 at the Rocketdyne facility in Canoga Park, California.
Concurrently with development of the H-1 engine, studies were conducted pertaining to the feasibility of a larger single-chamber rocket engine. On January 9, 1959, Rocketdyne agreed by contract to design, develop, and test such an engine, designated as the F-l. This engine, burning LOX and RP-1, a kerosene-type fuel, would generate a very high thrust, approximately 1,500,000 pounds.
Construction of the ABMA static test stand for large boosters began January 10, 1959. Meanwhile, Army representatives of the ARPA board visited AMR to discuss selection of a site for large vehicle launch facilities at Cape Canaveral, Florida. By February 1959, a contract had been awarded for construction of the blockhouse at the site (Launch Complex 34). A design contract was also awarded for a movable structure which would be used to assemble and service the vehicle on the launch pedestal.
On February 3 an ARPA memorandum officially renamed the large launch vehicle project Saturn. ARPA representatives presented the proposed National Vehicle Program to the President and the National Aeronautics and Space Council on March 2, 1959. Included were the proposed Saturn B and C vehicle systems. 5
On March 13 ABMA submitted to ARPA the results of the Saturn System Study. This study indicated that either an Atlas or a Titan could be used as the second stage of the proposed vehicle.6 During May ARPA decided that modified Titan hardware could be used for the second stage and that the third stage could use a slightly modified Centaur vehicle.
By April 28 the first production H-1 engine (H-1001) had been delivered on schedule to ABMA. ABMA's first firing test of this engine, later used in the first test booster, was performed successfully on May 26, 1959. 7
On July 5, 1959, construction of the Saturn blockhouse for Launch Complex 34 began at Cape Canaveral. On July 27 when the last Jupiter airframe was completed, Redstone Arsenal shops began retooling to support the Saturn project.
Late in July the Director of Defense Research and Engineering notified the Air Force and ARPA to consider common development of the Saturn second stage and the booster for the proposed Dyna Soar; requirements for these stages appeared to be similar. Until review of this, neither agency was to make a firm commitment for the redesign of .existing boosters or development of new ones.
ARPA then ordered cessation of the AOMC in-house and contractor work relating to the Titan second stage. An exception was made of some preliminary work not directly connected with the stage diameter. 8
Work continued on the Saturn booster stage. While studies of the proposed Saturn-Dyna Soar combination were in progress, ARPA, on August 1, authorized ABMA to proceed toward captive firing the Saturn booster early in 1960.
In September representatives of AOMC, NASA, and the Air Force presented Saturn, Nova, and Titan C systems to the Booster Evaluation Committee of the Office of the Secretary of Defense. On the basis of these presentations ARPA chose Saturn. ARPA then requested that Redstone scientists determine the Saturn configurations which could best carry NASA payloads.
During October 1959 consideration of Saturn vehicle configurations continued. On October 29 and 30 ABMA presented a second Saturn System Study to ARPA and National Aeronautics and Space Administration (NASA), proposing various upper-, stage configurations which offered increased pay-load capability and growth potential. In December 1959, after evaluation of previous presentations, NASA and ARPA requested that AOMC prepare an engineering study for a three-stage Saturn configuration.
Because of its large size and weight, the Saturn booster could not be transported by air or land. Water transportation appeared most feasible, and ARPA, on October 23, 1959, authorized AOMC to proceed with engineering work for dock facilities. These would be located on the Tennessee River at the southern boundary of Redstone Arsenal. In December AOMC was further authorized to construct the facilities and to build a barge to transport the booster to Cape Canaveral.
On November 18 NASA assumed technical direction of the Saturn project pending its formal transfer from ARPA. Administrative direction was retained by ARPA until March 16, 1960, when transfer of both administrative and technical direction would become effective.
On December 15 the Saturn Vehicle Evaluation Committee (the Silverstein Committee) reached a decision on Saturn upper-stage configurations. This committee, composed of representatives from NASA, ARPA, DOD, and the Air Force, recommended a long-range development program for a Saturn vehicle with upper-stage engines burning liquid hydrogen and liquid oxygen. The initial vehicle, identified as C-1, was to be a stepping stone to a larger vehicle, the C-2. A building-block concept was proposed that would yield a variety of Saturn configurations, each using previously proven developments as far as possible. These recommendations were accepted by the NASA Administrator. On December 31, 1959, a ten-vehicle program was established. 9
The C-l vehicle configuration included the S-1, the S-IV, and the S-V stages. The S-I stage would have eight H-1 engines. Fueled by LOX/RP-1, the engines clustered were expected to produce a total of 1,500,000 pounds of thrust. The S-IV stage was conceived of as a four-engine liquid oxygen-liquid hydrogen fueled unit capable of producing a total of 80, 000 pounds of thrust. The S-V stage would use two of the same engines as the S-IV stage and this stage would provide an additional 40, 000 pounds of thrust.
The Saturn project was approved on January 18, 1960, as a program of the highest national priority (DX rating).
To develop the second stage of Saturn C-l, NASA sought a contractor. A bidder's conference concerning this S-IV stage was held at Huntsville, January 26 and 27, 1960. By February 29 twelve companies had submitted contract proposals.
Redstone Arsenal scientists started to work on the first stage. By 1960 the formal test program to prove out the clustered booster concept was well under way. A mockup of the Saturn booster was installed in the ABMA test stand on January 4, 1960, to check mating of the booster and stand and to test servicing methods. This mockup was removed from the test stand and the complete test booster, SA-T, was installed in its place during February 1960.
During March the executive order transferring the Saturn program to NASA became effective.10 Later in the month two of Saturn's eight first-stage engines passed an initial static firing test of approximately eight seconds' duration. This test was identified as number SAT-01, the first live firing of the Saturn test booster (SA-T). It occurred on March 28.11 in a second test (SAT-02), on April 6, four engines were successfully static fired for seven seconds. All eight engines of the test booster were successfully fired on April 29 in an eight-second test.12
On May 17 a second eight-engine static firing of 24 seconds' duration generated a thrust of 1.3 million pounds. The third successful eight-engine firing lasted 35 seconds. 13
Meanwhile, NASA reviewed the S-IV proposals received in February. On April 26 NASA awarded Douglas Aircraft Company a contract to develop and build the second stage.
During May NASA announced that Rocketdyne had been selected to develop the high-thrust J-2 engine. This engine, of the type defined by the Silverstein Committee in December 1959, would burn liquid hydrogen-liquid oxygen. It would be used in an advanced Saturn vehicle.
The first ten Saturn flight vehicles would be numbered from SA-1 to SA-10. SA-10 would be the prototype of the operational Saturn.
On May 26, 1960, assembly of the booster stage for the first Saturn flight vehicle began in Huntsville.
On July 1, 1960, the Saturn program was formally transferred to the George C. Marshall Space Flight Center (MSFC). 14 A second series of static tests had just been successfully completed on the first stage of Saturn C-1.
On July 26 NASA signed a supplemental agreement with Douglas Aircraft Company covering the second stage. Douglas would design, develop, and fabricate the four-engine S-IV stage.