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Saturn C-4

Saturn C-4
Saturn C-4B on pad
FunctionLEO and Lunar launch vehicle
Manufacturer
Country of originUnited States
Cost per launch43.5 million
Cost per year1985
Size
Height269.0 ft (82.0 m)
Diameter320 in (8.1 m)
Mass1,023,670 lb (464,330 kg)
Stages3
Capacity
Payload to LEO
Mass218,000 lb (99,000 kg)
Payload to TLI
Mass70,000 lb (32,000 kg)
Associated rockets
FamilySaturn
ComparableSaturn V
Launch history
StatusProposed (1962)
Launch sitesplanned SLC 37, LC-39; Kennedy Space Center
First stage – S-IB-4
Height113.10 ft (34.47 m)
Diameter320 in (8.1 m)
Empty mass149,945 lb (68,014 kg)
Gross mass1,599,433 lb (725,491 kg)
Powered by4 Rocketdyne F-1
Maximum thrust6,000,000 lbf (27,000 kN)
Specific impulse265 sec (sea level)
Burn time139 seconds
PropellantRP-1/LOX
Second stage – S-II-4
Height69.80 ft (21.28 m)
Diameter320 in (8.1 m)
Empty mass54,978 lb (24,938 kg)
Gross mass449,840 lb (204,040 kg)
Powered by4 Rocketdyne J-2
Maximum thrust800,000 lbf (3,600 kN)
Specific impulse300 sec (sea level)
Burn time200 seconds
PropellantLH2 / LOX
Third stage – S-IVB
Height61.6 ft (18.8 m)
Diameter21.7 ft (6.6 m)
Empty mass29,700 lb (13,500 kg)
Gross mass271,000 lb (123,000 kg)
Powered by1 Rocketdyne J-2
Maximum thrust225,000 lbf (1,000 kN)
Specific impulse421 seconds (4.13 km/s)
Burn time165 + 335 seconds (2 burns)
PropellantLH2 / LOX
[edit on Wikidata]

The Saturn C-4 was the fourth rocket in the Saturn C series studied from 1959 to 1962. The C-4 design was proposed in 1960 for a three-stage launch vehicle that could launch 99,000 kg (218,000 lb) to low Earth orbit and send 32,000 kg (70,000 lb) to the Moon via trans-lunar injection. It met the initial requirements for a lunar orbit rendezvous and lunar landing mission.[1]

It would have consisted of three stages; an S-IB-4 first stage, a S-II-4 second stage and a S-IVB third stage. The first and second stages were essentially four-engine variants of the stages that would be used on the Saturn V, while the IVB stage was actually used on both the Saturn V and the Saturn IB.

It would have been capable of sending the 30,000 kg (67,000 lb) Apollo Command/Service Module into lunar orbit, but it would not have been able to carry the 15,000 kg (32,000 lb) Apollo Lunar Module as well. Although NASA eventually used the lunar orbit rendezvous method to go to the Moon, it decided to use the larger Saturn V which would provide a reserve payload capacity.

A December 1961 version called Saturn C-4B would have consisted of a S-IC C-4B first stage, a S-II C-5A second stage and a S-IVB C-5A third stage.[2] It would have been capable of sending a 31,000 kg (68,000 lb) payload to a translunar trajectory.[2]

See also

References

  1. ^ "Saturn C-4". Astronautix.com. Archived from the original on 17 June 2012. Retrieved 8 June 2012.
  2. ^ a b "Saturn C-4B". 2012-06-17. Archived from the original on 2012-06-17. Retrieved 2023-12-26.{{cite web}}: CS1 maint: bot: original URL status unknown (link)
  • Encyclopedia Astronautica Saturn C-4
  • 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.
  • 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).

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

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