A | B | C | D | E | F | G | H | CH | I | J | K | L | M | N | O | P | Q | R | S | T | U | V | W | X | Y | Z | 0 | 1 | 2 | 3 | 4 | 5 | 6 | 7 | 8 | 9
Manufacturer | Douglas Aircraft Company |
---|---|
Country of origin | United States |
Used on | Saturn I (stage 2) |
General characteristics | |
Height | 12.19 m (40.0 ft) |
Diameter | 5.49 m (18.0 ft) |
Gross mass | 50,576 kg (111,501 lb) |
Propellant mass | 45,359 kg (100,000 lb) |
Empty mass | 5,217 kg (11,500 lb) |
Launch history | |
Status | Retired |
Total launches | 6 |
Successes (stage only) | 6 |
Failed | 0 |
First flight | January 29, 1964 |
Last flight | July 30, 1965 |
S-IV 100 series | |
Powered by | 6 RL-10 engines |
Maximum thrust | 400 kN (90,000 lbf) |
Specific impulse | 410 s (4.0 km/s) |
Burn time | 482 s |
Propellant | LH2 / LOX |
The S-IV was the second stage of the Saturn I rocket used by NASA for early flights in the Apollo program.
The S-IV was manufactured by the Douglas Aircraft Company and later modified by them to the S-IVB, a similar but distinct stage used on the Saturn IB and Saturn V rockets.[1]
The S-IV stage was a large LOX/LH2-fueled rocket stage used for the early test flights of the Saturn I rocket. It formed the second stage of the Saturn I and was powered by a cluster of six RL-10A-3 engines. Each one of the engines supplied 66.7 kilonewtons (15,000 lbf) of thrust for a total of about 400 kilonewtons (90,000 lbf). The cryogenic LH2 (liquid hydrogen) and LOX (liquid oxygen) tanks were separated by a common bulkhead. The forward bulkhead of the LOX tank formed the aft bulkhead of the LH2 tank. This saved up to 20% of structural weight.[2][3]
References
- ^ Bilstein 1999, p. 157
- ^ Bilstein 1999, pp. 166-168
- ^ Apollo Summary Report 1975, p. 187
- Bilstein, Roger E. (1999). "6". Stages to Saturn: A Technological History of the Apollo/Saturn Launch. DIANE Publishing. ISBN 9780788181863. Retrieved 2010-05-04.
- NASA (April 1975). "Apollo Program Summary Report (Large file)" (PDF).
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