The first Saturn I was launched October 27, 1961
|Function||Manned LEO launch vehicle|
Convair (S-V) - Unflown
|Country of origin||United States|
|Height||55 m (180 ft)|
|Diameter||6.52 m (21.39 ft)|
|Mass||509,660 kg (1,123,600 lb)|
|Stages||2 or 3
(3rd stage never flown)
|Payload to LEO||9,000 kg (2 stage)|
|2,200 kg (2 stage)|
|Launch sites||LC-37 & LC-34, Cape Canaveral|
|Maiden flight||October 27, 1961|
|Last flight||July 30, 1965|
|Notable payloads||Apollo CSM (boilerplate)
|First stage - S-I|
|Thrust||6.7 MN (1,500,000 lbf)|
|Burn time||~150 seconds|
|Second stage - S-IV|
|Thrust||400 kN (90,000 lbf)|
|Burn time||~482 seconds|
|Third stage - S-V (Centaur-C) - unflown|
|Thrust||133 kN (30,000 lbf)|
|Burn time||~430 seconds|
The Saturn I was the United States' first dedicated "space launcher," a rocket designed specifically to launch loads into Earth's orbit. Most of the rocket's power came from a "clustered" lower stage consisting of tanks taken from older rocket designs and strapped together to make a single larger booster. Critics joked that it was "Cluster's Last Stand", but the Saturn design proved sound and very flexible. Originally intended to be an almost universal military booster during the 1960s, it served only for a brief period and only with NASA; ten Saturn I's were flown before it was replaced by the Saturn IB, which featured a more powerful upper stage.
The Saturn project was started as one of a number of proposals to meet a new Department of Defense (DoD) requirement for a heavy-lift vehicle to orbit a new class of communications and "other" satellites. The requirements, drawn up by the then-unofficial Advanced Research Projects Agency (ARPA), called for a vehicle capable of putting 9,000 to 18,000 kilograms into orbit, or accelerating 2,700 to 5,400 kg to escape velocity. Existing launchers could place a maximum of about 1,400 kg in orbit, but might be expanded to as much as 4,500 kg with new high-energy upper stages. In any event, these upper stages would not be available until 1961 or 62 at the earliest, and would still not meet the DoD requirements for heavy loads.
Wernher von Braun's team at the U.S. Army Ballistic Missile Agency (ABMA) started studying the problem in April 1957. They calculated that a rocket with the required performance would require a lower stage booster with a thrust of about 1.5 million pound-force (6.7 MN) thrust at takeoff. As it happened, the Air Force had recently started work on just such an engine, eventually emerging as the F-1, but this would not be available in the time frame that the DoD was demanding and would be limited to about 1 million lbf in the short term anyway. Another possibility was a Rocketdyne engine, then known as the E-1, which provided about 360,000 to 380,000 lbf, four of which would reach the required thrust levels. This approach became the favorite, and in order to quickly provide fuel tankage to supply the engines, a new stage consisting of the tank from a Jupiter wrapped with eight taken from the Redstone would be used along with a thrust plate on the bottom where the engines would be attached.
Von Braun returned the design to ARPA in December, 1957 as A National Integrated Missile and Space Vehicle Development Program, outlining the new design, then known simply as "Super-Jupiter". Several variations were proposed, using a common clustered first stage, and upper stages based on either the Atlas or Titan I. ABMA favored the Titan as the Atlas production was extremely high-priority and there was little or no excess capacity to spare. They proposed using the existing Titan tooling at 120" diameter, but lengthening it to produce a new 200-foot-long stage. A Centaur would be used as a third stage, which was expected to be ready for operational use in 1963, right when the lower two stages would have completed their testing. The resulting three-stage design was much taller and skinnier than the Saturn design that was eventually built.
ARPA, which became official in February 1958, asked for only one change to the design; concerned that the E-1 was still in early development, in July they suggested looking at alternatives in order to ensure the rocket would enter production as soon as possible. ABMA quickly responded with a slightly modified design replacing the four E-1's with eight H-1 engines, a minor upgrade to the S-3D engine used on Thor and Jupiter missiles. They estimated that changing the engines would save about $60 million and as much as two years research and development time. Von Braun had earlier referred to Redstone and Jupiter rockets being used as space launchers as the Juno I and Juno II, respectively, and made proposals for multi-stage versions as the Juno III and IV, and so he changed the name of the new design to Juno V. The total development cost of $850 million ($5.6 billion in year-2007 dollars) between 1958-1963 also covered 30 research and development flights, some carrying manned and unmanned space payloads.
Satisfied with the outcome, ARPA Order Number 14-59, dated 15 August 1958, ordered the program into existence:
This was followed on 11 September 1958 with another contract with Rocketdyne to start work on the H-1. On 23 September 1958, ARPA and the Army Ordnance Missile Command (AOMC) drew up an additional agreement enlarging the scope of the program, stating "In addition to the captive dynamic firing..., it is hereby agreed that this program should now be extended to provide for a propulsion flight test of this booster by approximately September 1960." Further, they wanted ABMA to produce three additional boosters, the last two of which would be "capable of placing limited payloads in orbit."
Von Braun had high hopes for the design, feeling it would make an excellent test-bed for other propulsion systems, notably the F-1 if it matured. He outlined uses for the Juno V as a general carrier vehicle for research and development of "offensive and defensive space weapons." Specific uses were forecast for each of the military services, including navigation satellites for the Navy; reconnaissance, communications, and meteorological satellites for the Army and Air Force; support for Air Force manned missions; and surface-to-surface logistics supply for the Army at distances up to 6400 kilometers. Von Braun also proposed using the Juno V as the basis of a manned lunar mission as part of Project Horizon. Juno could lift up to 20,000 pounds (9,000 kg) into low earth orbit, and he proposed launching 15 of them to build a 200,000-lb lunar spacecraft in Earth orbit.
Even by this point the name "Saturn", as "the one after Jupiter" was being used. One early ARPA report noted "The SATURN is considered to be the first real space vehicle as the Douglas DC-3 was the first real airliner and durable work-horse in aeronautics." The name change became official in February 1959.
The formation of NASA on July 29, 1958 led to an effort to collect the existing heavy-launch rocket programs and select a single set of designs for future work. At the time, both the Air Force and US Army had teams developing such vehicles, the Army's Saturn and the Air Force's Space Launching System (SLS). The SLS used a set of common modular components with solid fuel boosters and hydrogen/oxygen upper stages to allow a wide variety of launch configurations and payload weights. Both groups had also developed plans for manned lunar bases, ABMA's Horizon with its Earth Orbit Rendezvous method of building a large lunar rocket in Earth orbit, and the Air Force's Lunex Project which planned on launching a single huge lander using the largest of the SLS configurations. As if this were not enough, NASA's own engineers had started the design of their own Nova design series, planning to use it in the direct ascent profile similar to the Air Force's approach.
Von Braun was asked to chair a committee to study the existing efforts and write up recommendations. They presented their report on 18 July, starting with a criticism of how the US program had been mishandled to date and pointing out that the Soviet program was definitely ahead. It went on to describe five "generations" of rockets, starting with the early Vanguard, through the Junos, ICBMs like Atlas and Titan, clustered designs like the Saturn, and finally the ultimate development, a cluster using the F-1 with 6 million pounds of thrust. The report went on to outline a manned exploration program using these rockets as they became available; using existing ICBM's a small four-man space station could be operational 1961, the clusters would support a manned lunar landing in 1965-1966 and a larger 50-man space station by 1967, while the largest of the rockets would support large moon expeditions in 1972, set up a permanent moon base in 1973-1974, and launch manned interplanetary trips in 1977.
In December all of the teams gathered to present their designs. NASA selected von Braun's proposal on January 6th, giving it a vital boost. At the end of January NASA outlined their complete development program. This included the Vega and Centaur upper stages, as well as the Juno V and their own Nova boosters. Vega was later cancelled when information on the formerly secret Agena upper stage was released (then known as "Hustler"), and it had performance roughly comparable to NASA's design.
Progress on the Saturn design seemed to go smoothly. In April the first H-1 engines started arriving at ABMA, and test firings started in May. Construction of the Complex 34 launch sites started at Cape Canaveral in June.
Then, quite unexpectedly, on 9 June 1959, Herbert York, Director of Department of Defense Research and Engineering, announced that he had decided to terminate the Saturn program. He later stated that he was concerned that the project was taking ARPA money from more pressing projects, and that as it seemed upgrades to existing ICBMs would provide the needed heavy-lift capability in the short term. As ABMA commander John B. Medaris put it:
Looking to head off the cancellation, Saturn supporters from the DoD and ARPA drafted their own memo arguing against the cancellation. Working against them was the fact that neither the Army nor NASA had any in-writing requirement for the booster at that time. A three-day meeting between 16 and 18 September 1959 followed, where York and Dryden reviewed Saturn's future and discussed the roles of the Titan C and Nova. The outcome was equally unexpected; York agreed to defer the cancellation and continue short-term funding, but only if NASA agreed to take over the ABMA team and continue development without the help of the DoD. NASA was equally concerned that by relying on 3rd parties for their boosters they were putting their entire program in jeopardy.
As the parties continued discussions over the next week and agreement was hammered out; von Braun's team at ABMA would be kept together and continue working as the lead developers of Saturn, but the entire organization would be transferred to NASA's management. By a presidential executive order on 15 March 1960, ABMA became NASA's George C. Marshall Space Flight Center (MSFC).
In July 1959 a change request was received from ARPA to upgrade the upper stage to a much more powerful design using four new 20,000-lbf liquid hydrogen/liquid oxygen powered engines in a larger-diameter 160" second stage, with an upgraded Centaur using two engines of the same design for the third stage. On this change Medaris noted:
In order to reach some sort of accommodation, a group pulled from NASA, Air Force, ARPA, ABMA, and the Office of the Department of Defense Research and Engineering formed under the Silverstein Committee in December. Originally skeptical, the Committee convinced von Braun that liquid hydrogen was the way to go on upper stage development. Once these changes had been made, NASA's booster project was now entirely free of any dependence on military developments. At that point any sort of upper stage was fair game, and "If these propellants are to be accepted for the difficult top-stage applications," the committee concluded, "there seem to be no valid engineering reasons for not accepting the use of high-energy propellants for the less difficult application to intermediate stages."
The Committee outlined a number of different potential launch configurations, grouped into three broad categories. The "A" group were low-risk versions similar to the Saturn designs proposed prior to the meeting; the original design using Titan and Centaur upper stages became the A-1, while another model replacing the Titan with cluster of IRBMs became A-2. The B-1 design proposed a new second stage replacing the A-2s cluster with a new four-engine design using the H-1 like the lower stage. Finally there were three C-series models that replaced all of the upper stages with liquid hydrogen ones. The C-1 used the existing S-I clustered lower, adding the new S-IV stage with four new 15,000 to 20,000 lbf engines, and keeping the two-engine Centaur on top, now to be known as the S-V stage. The C-II model added a new S-III stage with two new 150,000 to 200,000 lbf engines, keeping the S-IV and S-V on top. Finally, the C-3 configuration added the S-II stage with four of these same engines, keeping only the S-III and S-IV on top. The C models easily outperformed the A's and B's, with the added advantage that they were interchangeable and could be built up in order to fit any needed payload requirement.
Ironically, of these new stage designs only the S-IV would ever be delivered, and not in the form that was drawn up in the Committee report. In order to meet development schedules a cluster of six Centaur engines were placed in the new 220" stage to produce the "new" S-IV of roughly the same performance as the original four upgraded engines. A large number of small engines is less efficient and more problematic than a smaller number of large engines, and this made it a target for an early upgrade to a single J-2. The resulting stage, the S-IVB, improved performance so much that the Saturn was able to launch the Apollo CSM, proving invaluable during the Apollo Project.
In the end the Titan C was never delivered, and the Air Force instead turned to "thrust augmented" Titan II's using clustered solid fuel rockets. These new designs, the Titan III's, became the workhorse of the Department of Defense's launch needs. A Titan III has about the same lift capability as a Saturn IB but costs less to manufacture and launch. Likewise, the development of the Titan III eliminated the need for the "flexible" staging concepts of the Saturn, which was now only intended to be used for manned launches in the Apollo program. With the need for flexibility in launch configuration removed, most of these designs were subsequently dropped. Only the S-V survived in its original form, while the S-IV would appear in modified form and the Saturn V would feature an entirely different S-II stage.
The main payload of the Saturn I was the boilerplate version of the Apollo spacecraft. It was also considered at one time for launch of the X-20 Dyna-Soar spaceplane and later, for launching a Gemini capsule on a proposed lunar mission. The final three were used to launch the three Pegasus satellites.
|Parameter||S-I - 1st Stage||S-IV - 2nd Stage||S-V - 3rd Stage|
|Gross mass (kg)||432,681||50,576||15,600|
|Empty mass (kg)||45,267||5,217||1,996|
|Engines||Eight - H-1||Six - RL10||Two - RL10|
|Burn duration (s)||150||482||430|
The S-I was an eight-engine first-stage rocket booster. Each S-I was composed of nine propellant containers, eight fins, a thrust structure assembly, eight H-1 rocket engines, and many other components. The propellant containers consisted of eight Redstone tanks, four holding LOX, painted white, and four holding RP-1, painted black. They were clustered around a central Jupiter rocket tank, which contained LOX. The four outboard engines could gimbal, meaning they could be steered to properly guide the rocket. This required a few more engine components.
Height: 24.48 m
Diameter: 6.52 m
Engines: 8 H-1
Thrust: 1,600,000 lbf (7.1 MN)
Fuel: RP-1 (Refined kerosene) 41,000 US gal (155 m³)
Oxidizer: liquid oxygen (LOX) 66,000 US gal (250 m³)
Burn time: 2.5 min
Burnout altitude: 42 miles (68 km)
The S-IV stage is a large Lox/LH2-fueled rocket stage. It is powered by six RL10 engines, which can gimbal. This stage has a "common bulkhead," meaning that one propellant tank is directly connected to the other. This saves about ten tons of weight.
Saturn I Block I vehicles (SA-1 to SA-4) were guided by instruments carried in canisters on top of the S-I first stage, and included the ST-90 stabilized platform, made by Ford Instrument Company and used in the Redstone missile.  These first four vehicles followed ballistic, non-orbital trajectories, and the dummy upper stages did not separate from the single powered stage.
The Block II vehicles (SA-5 to -10) included two powered stages, and went into orbits. Beginning with SA-5, the guidance instruments were carried on a separate stage, the instrument unit (IU), just ahead of the S-IV stage. The first version of the IU was 154 inches (3,900 mm) in diameter and 58 inches (1,500 mm) high, and was both designed and built by Marshall Space Flight Center. Guidance, telemetry, tracking and power components were contained in four pressurized, cylindrical containers attached like spokes to a central hub.  This version flew on SA-5, 6, and 7.
MSFC flew version 2 of the IU on SA-8, 9 and 10. Version 2 was the same diameter as version 1, but only 34 inches (860 mm) high. Instead of pressurized containers, the components were hung on the inside of the cylindrical wall, achieving a reduction in weight. 
The guidance computer for Block II was the IBM ASC-15. Other instruments carried by the IU included active components, that guided the vehicle; and passenger components, that telemetered data to the ground for test and evaluation for use in later flights. The ST-90 stabilized platform was the active IMU for SA-5 and the first stage of SA-6. The ST-124 was the passenger on SA-5 and active for the second stage of SA-6 and subsequent missions. The IU had an optical window to allow alignment of the inertial platform before launch.
|Serial number||Mission||Launch date||Notes|
|SA-1||SA-1||October 27, 1961||First test flight. Block I. Suborbital. Range 398 km, Apogee 136.5 km. Apogee Mass 115,700 lb (52,500 kg).|
|SA-2||SA-2||April 25, 1962||Second test flight. Block I. Suborbital. 86,000 kg water released at apogee of 145 km.|
|SA-3||SA-3||November 16, 1962||Third test flight. Block I. Suborbital. 86,000 kg water released at apogee of 167 km.|
|SA-4||SA-4||March 28, 1963||Fourth test flight. Block I. Suborbital. Dummy SIV 2nd stage. Apogee 129 km, range 400 km.|
|SA-5||SA-5||January 29, 1964||First live S-IV 2nd stage. Block II. Orbit 760 by 264 km. Mass 38,700 lb (17,550 kg). Decayed 30 April 1966.|
|SA-6||A-101||May 28, 1964||First Apollo boilerplate launch. Block II. Orbit 204 by 179 km. Mass 38,900 lb (17,650 kg). Apollo BP-13 Decayed 1 June 1964.|
|SA-7||A-102||September 18, 1964||Second Apollo boilerplate launch. Block II. Orbit 203 by 178 km. Mass 36,800 lb (16,700 kg). Apollo BP-15 Decayed 22 September 1964.|
|SA-9||A-103||February 16, 1965||First Pegasus Micrometeoroid Satellite. Orbit 523 by 430 km. Mass 3,200 lb (1,450 kg). Pegasus 1 Decayed 17 September 1978. Apollo BP-26 Decayed 10 July 1985.|
|SA-8||A-104||May 25, 1965||Second Pegasus Micrometeoroid Satellite. Orbit 594 by 467 km. Mass 3,200 lb (1,450 kg). Pegasus 2 Decayed 3 November 1979. Apollo BP-16 Decayed 8 July 1989.|
|SA-10||A-105||July 30, 1965||Third Pegasus Micrometeoroid Satellite. Orbit 567 by 535 km. Mass 3,200 lb (1,450 kg). Pegasus 3 Decayed 4 August 1969. Apollo BP-9A Decayed 22 November 1975.|