 Schematics of the S-IV | |
| 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]
- ^ Bilstein 1999, p. 157
- ^ Bilstein 1999, pp. 166-168
- ^ Apollo Summary Report 1975, p. 187