Saturn C-4

Saturn C-4

Function	LEO and Lunar launch vehicle
Manufacturer	Boeing (S-IB) North American (S-II) Douglas (S-IV)
Country of origin	United States
Cost per launch	43.5 million (1985)
Size
Height	269.0 feet (82.0 m)
Diameter	320 inches (8.1 m)
Mass	1,023,670 pounds (464,330 kg)
Stages	3
Capacity
Payload to LEO	218,000 pounds (99,000 kg)
Payload to TLI	70,000 pounds (32,000 kg)
Associated rockets
Family	Saturn
Comparable	Saturn V
Launch history
Status	Proposed (1962)
Launch sites	planned SLC 37, Kennedy Space Center
First stage - S-IB-4
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	4 Rocketdyne F-1
Thrust	6,000,000 pounds-force (27,000 kN)
Specific impulse	265 sec (sea level)
Burn time	139 seconds
Fuel	RP-1/LOX
Second stage - S-II-4
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-IVB
Length	61.6 feet (18.8 m)
Diameter	21.7 feet (6.6 m)
Empty mass	29,700 pounds (13,500 kg)
Gross mass	271,000 pounds (123,000 kg)
Engines	1 Rocketdyne J-2
Thrust	225,000 lbf (1,000 kN)
Specific impulse	421 seconds (4.13 km/s)
Burn time	165 + 335 seconds (2 burns)
Fuel	LH2/LOX

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.

See also

• Saturn C-3
• List of space launch system designs

References

1. "Saturn C-4". Astronautix.com. Retrieved 8 June 2012.

• 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).

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