Saturn C-3

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Saturn C-3
Proposed Saturn C-3 Apollo Configuration.jpg
Proposed Saturn C-3 and Apollo configuration (1962)
Function LEO and Lunar launch vehicle
Manufacturer Boeing (S-IB-2)
North American (S-II-C3)
Douglas (S-IV)
Country of origin United States
Cost per launch 43.5 million
Height 269.0 feet (82.0 m)
Diameter 320 inches (8.1 m)
Mass 1,023,670 pounds (464,330 kg)
Stages 3
Payload to
100,000 pounds (45,000 kg)
Payload to
39,000 pounds (18,000 kg)
Associated rockets
Family Saturn
Derivatives Saturn INT-20, Saturn INT-21
Comparable Falcon Heavy, Delta IV Heavy
Launch history
Status Proposed (1961)
Launch sites planned SLC 37, Kennedy Space Center
First Stage - S-IB-2
Length 113.10 feet (34.47 m)
Diameter 320 inches (8.1 m)
Empty mass 149,945 pounds (68,014 kg)
Gross mass 1,599,433 pounds (725,491 kg)
Engines 2 Rocketdyne F-1
Thrust 3,000,000 pounds-force (13,000 kN)
Specific impulse 265 sec (sea level)
Burn time 139 seconds
Fuel RP-1/LOX
Second Stage - S-II-C3
Length 69.80 feet (21.28 m)
Diameter 320 inches (8.1 m)
Empty mass 54,978 pounds (24,938 kg)
Gross mass 449,840 pounds (204,040 kg)
Engines 4 Rocketdyne J-2
Thrust 800,000 pounds-force (3,600 kN)
Specific impulse 300 sec (sea level)
Burn time 200 seconds
Fuel LH2/LOX
Third Stage - S-IV
Length 61.6 feet (18.8 m)
Diameter 220 inches (5.6 m)
Empty mass 11,501 pounds (5,217 kg)
Gross mass 111,500 pounds (50,600 kg)
Engines 6 Rocketdyne RL-10
Thrust 90,000 pounds-force (400 kN)
Specific impulse 410 sec
Burn time 482 seconds
Fuel LH2/LOX

The Saturn C-3 was the third rocket in the Saturn C series studied from 1959 to 1962. The design was for a three-stage launch vehicle that could launch 45,000 kg (100,000 lb) to low Earth orbit and send 18,000 kg (39,000 lb) to the Moon via Trans-Lunar Injection.[1]

President Kennedy's proposal on May 25, 1961 of an explicit manned lunar landing goal spurred NASA to concretize its launch vehicle requirements for a lunar landing. A week earlier, William Fleming (Office of Space Flight Programs, NASA Headquarters) chaired an ad hoc committee to conduct a six-weeks study of the requirements for a lunar landing. Judging the direct ascent approach to be the most feasible, they concentrated their attention accordingly, and proposed circumlunar flights in late 1965 using the Saturn C-3 launch vehicle.

In early June 1961, Bruce Lundin, deputy director of the Lewis Research Center, led a week-long study of six different rendezvous possibilities. The alternatives included earth-orbital rendezvous, lunar-orbital rendezvous, earth and lunar rendezvous, and rendezvous on the lunar surface, employing Saturn C-1s, C-3s, and Nova designs. Lundin's committee concluded that rendezvous enjoyed distinct advantages over direct ascent and recommended an earth-orbital rendezvous using two or three Saturn C-3s.[2]

NASA announced on September 7, 1961 that the government-owned Michoud Ordnance Plant near New Orleans, LA, would be the site for fabrication and assembly of the Saturn C-3 first stage as well as larger vehicles in the Saturn program. Finalists were two government-owned plants in St. Louis and New Orleans. The height of the factory roof at Michoud meant that a launch vehicle with eight F-1 engines (Nova class, Saturn C-8) could not be built; four or five engines would have to be the maximum.

This decision ended consideration of a Nova class launch vehicle for Direct Ascent to the Moon or as heavy-lift companion with the Saturn C-3 for Earth Orbit Rendezvous.

Lunar mission design[edit]

Earth Orbit Rendezvous[edit]

The Marshall Space Flight Center in Huntsville, Alabama developed an Earth Orbit Rendezvous proposal (EOR) for the Apollo program in 1960-1961. The proposal used a series of small rockets half the size of a Saturn V to launch different components of a spacecraft headed to the Moon. These components would be assembled in orbit around the Earth, then sent to the Moon via trans-lunar injection. In order to test and validate the feasibility of the EOR approach for the Apollo program, Project Gemini was founded with this objective:
To effect rendezvous and docking with another vehicle (Agena target vehicle), and to maneuver the combined spacecraft using the propulsion system of the target vehicle.

The Saturn C-3 was the primary launch vehicle for Earth Orbit Rendezvous. The booster consisted of a first stage containing two Saturn V F-1 engines, a second stage containing four powerful J-2 engines, and the S-IV stage from a Saturn I booster. Only the S-IV stage of the Saturn C-3 was developed and flown, but all of the specified engines were used on the Saturn V rocket which took men to the moon.[3]

Lunar Orbit Rendezvous[edit]

The concept of Lunar Orbit Rendezvous (LOR) was studied at Langley Research Center as early as 1960. John Houbolt's memorandum advocating LOR for lunar missions in November 1961 to Robert Seamans outlined the usage of the Saturn C-3 launch vehicle, and avoiding complex large boosters and lunar landers.[4]

After six months of further discussion NASA, in the summer of 1962, selected the Lunar Orbit Rendezvous (LOR) proposal from Langley Research Center for the Apollo program.[5] By the end of 1962, the Saturn C-3 design was deemed not necessary for Apollo program requirements as larger boosters (Saturn C-4, Saturn C-5) were then proposed, hence further work on the Saturn C-3 was cancelled.[6]

Variants and derivatives[edit]

Saturn C-3B versions, with a nuclear upper stage derivative (1961)

Since 1961 a number of variants of the Saturn C-3 have been studied, proposed, and funded. The most extensive studies focused on the Saturn C-3B variants before end of 1962, when Lunar Orbit Rendezvous was selected and Saturn C-5 development approved. The common theme of these variants is the use of two or three Rocketdyne F-1 engines in a S-IB-2 or S-1C stage with diameters ranging from 8 to 10 meters (27 to 33 feet) that could lift up to 110,000 pounds (50,000 kg) to Low Earth Orbit (LEO).

The lack of a Saturn C-3 launch vehicle in 1965 created a large payload gap (LEO) between the Saturn IB's 19,000 kg low-earth orbit capacity and the two-stage Saturn V's 100,000 kg capability. In the mid-1960s NASA's Marshall Space Flight Center (MSFC) initiated several studies to fill this payload capacity gap and to extend the capabilities of the Saturn family. Three companies provided proposals to MSFC for this requirement. Martin Marietta (builder of Atlas, Titan vehicles), Boeing (builder of S-1B and S-1C first stages) and North American (builder of the S-II second stage).

Saturn C-3B[edit]

The Saturn C-3B revision (1961) increased the total thrust of the three stages to 17,200 kN.
The diameter of the first stage (S-IB-2) was increased to 33 feet (10 meters). The eventual first stage for the Saturn V (S-IC) would use this same diameter, but add 8 meters to its length. A further consideration added a third F-1 engine to the first stage.

The S-II, second stage diameter would be 8.3 meters (326 inches) and 21.3 meters (70 feet) in length. The S-IV, third stage diameter would be 5.5 meters and 12.2 meters in length.

Saturn C-3BN[edit]

Main article: NERVA

The Saturn C-3BN revision (1961) would use the NERVA for the third stage in this launch vehicle. The NERVA technology has been studied and proposed since mid-1950s for future space exploration.

Saturn INT-20C, Boeing proposal (1966)

Saturn INT-20[edit]

Main article: Saturn INT-20

On October 7, 1966 Boeing submitted a Final Report to the NASA Marshall Space Flight Center, "Studies of Improved Saturn V Vehicles and Intermediate Payload Vehicles". That report outlined the Saturn INT-20, an intermediate two-stage launch vehicle with a S-1C first stage using three or four F-1 engines, and a S-IVB as the second stage with one J-2 engine. The vehicle's payload capacity for LEO would be 45,000 to 60,000 kg, comparable to the earlier Saturn C-3 design (1961). Boeing projected delivery and first flight in 1970, based on a decision by 1967.

Post-Apollo development[edit]

The need for a launch vehicle of Saturn C-3 capacity (45 metric tons to LEO) continued beyond the Apollo program. Cape Canaveral Air Force Station Space Launch Complex 37, initially designed to serve the Saturn I and I-B, was planned for eventual Saturn C-3 usage, but it was deactivated in 1972. In 2001, Boeing refurbished the complex for its Delta IV EELV launch vehicle. The Delta IV Heavy variant can only launch 22.5 metric tons to LEO.

The 1986 Space Shuttle Challenger disaster and 2010 Space Launch System program resulted in renewed proposals for Saturn C-3 derivatives using the Rocketdyne F-1A engines with existing booster cores and tooling (10m - Saturn S-IC stage; 8.4m - Space Shuttle external tank; 5.1m - Delta IV Common Booster Core).


Main article: Jarvis (rocket)

After the Space Shuttle Challenger disaster, the United States Air Force (USAF) and National Aeronautics and Space Administration (NASA) conducted a joint Advanced Launch System study (1987-1990). Hughes Aircraft and Boeing dusted off the earlier Saturn C-3 design and submitted their proposal for the Jarvis launch vehicle.
The Jarvis would be a three-stage rocket, 58 m (190 ft) in height and 8.38 m (27.5 ft) in diameter. Designed to lift 38 tons to LEO, it would utilize F-1 and J-2 rocket engines and tooling in storage from the Saturn V rocket program along with more recent Shuttle-era technologies to provide lower launch costs.[7]


As of April 2012, Dynetics announced they are teaming up with Pratt & Whitney Rocketdyne to resurrect the Saturn V rocket's mighty F-1 engine to power NASA's Space Launch System planned heavy-lift launch vehicle, saying the Apollo-era engine will offer significantly more performance than solid-fueled boosters currently under development. Dynetics of Huntsville, AL, is leading the contractor team proposing the F-1 engine design. Pratt & Whitney Rocketdyne is the bid's propulsion partner and engine builder. Cook, NASA's former manager of the scrapped Ares rocket program, said each of the two Dynetics boosters, on an SLS mission would be propelled by a pair of RP-1/LOX F-1Bs, an advanced variant of the F-1, (1.5million pounds of thrust) which was used on the Saturn V, and the F-1A. Developed during the later stages of the Apollo program, the F-1A was test fired, but never flew. Several were crated and stored by Rocketdyne (later Pratt & Whitney Rocketdyne). The company has also maintained an F-1/F-1A knowledge retention program for its engineers for the entire period the engine has been mothballed. Dynetics is now performing tests on engine components pulled from storage."Each of those engines (F-1A) can get up to 1.8 million pounds of thrust (8,000 kN)," Cook said in an interview Wednesday. "This booster is a very simple, very standard booster. It's 18 feet (5.5 m) in diameter. It uses the same attach points as the current five-segment solid rocket booster." [8]
The Dynetics booster would attach at these points, in the SLS parallel staging design, which differs from the Saturn rockets' serial staging design. Because it applies thrust to an upper thrust beam in the SLS core, it lifts at the top rather than at the bottom (Saturn S-IC stage had a thrust structure). The proposed Dynetics booster is similar to the first stage of the Saturn C-3 in that it would employ two F-1 heritage engines.[9][10]

See also[edit]


Inline citations
  1. ^ "Saturn C-3". Retrieved 8 June 2012. 
  2. ^ Benson, Charles D.; William Barnaby Faherty (1978). "4-8". Moonport: A History of Apollo Launch Facilities and Operations. NASA (SP-4204). Retrieved 7 February 2013. 
  3. ^ Bilsten, Roger E. (1980). Stages to Saturn. NASA SP-4206. pp. 48–63. 
  4. ^ Bilsten, Roger E. (1980). Stages to Saturn. NASA SP-4206. p. 63. 
  5. ^ "The Rendezvous That Was Almost Missed: Lunar Orbit Rendezvous and the Apollo Program". NASA Langley Research Center. December 1992. Retrieved 8 June 2012. 
  6. ^ David M. Reeves; Michael D. Scher; Dr. Alan W. Wilhite; Dr. Douglas O. Stanley (2005). "The Apollo Lunar Orbit Rendezvous Architecture Decision Revisited" (PDF). National Institute of Aerospace, Georgia Tech. Retrieved 8 June 2012. 
  7. ^ "Jarvis launch vehicle". Retrieved 8 June 2012. 
  8. ^ Stephen Clark (18 April 2012). "Rocket companies hope to repurpose Saturn 5 engines". Spaceflight Now. Retrieved 9 June 2012. 
  9. ^ Chris Bergin (9 November 2012). "Dynetics and PWR aiming to liquidize SLS booster competition with F-1 power". Retrieved 2 March 2013. 
  10. ^ Lee Hutchinson (14 April 2013). "New F-1B rocket engine upgrades Apollo-era design with 1.8M lbs of thrust". ars technica. 
  • Bilstein, Roger E, Stages to Saturn, US Government Printing Office, 1980. ISBN 0-16-048909-1. Excellent account of the evolution, design, and development of the Saturn launch vehicles.
  • Stuhlinger, Ernst, et al., Astronautical Engineering and Science: From Peenemuende to Planetary Space, McGraw-Hill, New York, 1964.
  • Jet Propulsion Lab; NASA Report - October 2, 1961; Some Interrelationships and Long Range Implications of C-3 Lunar Rendezvous and solid Nova vehicle concepts. Accessed at:
  • Robert P. Smith, Apollo Projects Office, NASA Report, Project Apollo - A description of a Saturn C-3 and Nova vehicle. July 25, 1961. Accessed at:
  • NASA, "Earth Orbital Rendezvous for an Early Manned Lunar Landing," pt. I, "Summary Report of Ad Hoc Task Group Study" [Heaton Report], August 1961.
  • David S. Akens, Saturn Illustrated Chronology: Saturn's First Eleven Years, April 1957 through April 1968, 5th ed., MHR-5 (Huntsville, AL : MSFC, 20 Jan. 1971).
  • Boeing Study, Marshall Space Flight Center, '"Final Report - Studies of Improved Saturn V Vehicles and Intermediate Payload Vehicles'", October 7, 1966 Accessed at:

 This article incorporates public domain material from websites or documents of the National Aeronautics and Space Administration.