| S-IV | |||||||||||||
| Manufacturer: | Douglas Aircraft Company | ||||||||||||
| Country: | United States | ||||||||||||
| Rockets: | Saturn I (stage 2) | ||||||||||||
| Height: | 12.19m (39.99feet) | ||||||||||||
| Diameter: | 5.49m (18.01feet) | ||||||||||||
| Mass: | 50576kg (111,501lb) | ||||||||||||
| Propmass: | 45359sigfig=3NaNsigfig=3 | ||||||||||||
| Empty: | 5217sigfig=3NaNsigfig=3 | ||||||||||||
| Status: | Retired | ||||||||||||
| Launches: | 6 | ||||||||||||
| Success: | 6 | ||||||||||||
| Fail: | 0 | ||||||||||||
| First: | January 29, 1964 | ||||||||||||
| Last: | July 30, 1965
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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.
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 of thrust for a total of about . 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.
| SA-1 | October 27, 196115:06:04 | First test flight. Block I. Suborbital. Range: 398 km. Apogee: 136.5 km. Apogee Mass: 115,700 lb (52,500 kg). Dummy S-IV and S-V stages. | |
| SA-2 | April 25, 196214:00:34 | Second test flight. Block I. Suborbital. 86,000 kg water released at apogee of 145 km as part of Project Highwater. Dummy S-IV and S-V stages. | |
| SA-3 | November 16, 196217:45:02 | Third test flight. Block I. Suborbital. 86,000 kg water released at apogee of 167 km. Dummy S-IV and S-V stages. Second and last Project Highwater flight. | |
| SA-4 | March 28, 196320:11:55 | Fourth test flight. Block I. Suborbital. Dummy S-IV second stage and S-V third stage. Apogee: 129 km. Range: 400 km. | |
| SA-5 | January 29, 196416:25:01 | First live S-IV second stage. First Block II. First to orbit: 760 x 264 km. Mass: 38,700 lb (17,550 kg). Decayed 30 April 1966. | |
| SA-6 | May 28, 196417:07:00 | First Apollo boilerplate CSM launch. Block II. Orbit: 204 x 179 km. Mass: 38,900 lb (17,650 kg). Apollo BP-13 decayed 1 June 1964. | |
| SA-7 | September 18, 196416:22:43 | Second Apollo boilerplate CSM launch. Block II. Orbit: 203 x 178 km. Mass: 36,800 lb (16,700 kg). Apollo BP-15 decayed 22 September 1964. | |
| SA-9 | February 16, 196514:37:03 | Third Apollo boilerplate CSM. First Pegasus micrometeoroid satellite. Orbit: 523 x 430 km. Mass: 3,200 lb (1,450 kg). Pegasus 1 decayed 17 September 1978. Apollo BP-26 decayed 10 July 1985. | |
| SA-8 | May 25, 196507:35:01 | Fourth Apollo boilerplate CSM. Only night launch. Second Pegasus micrometeoroid satellite. Orbit: 594 x 467 km. Mass: 3,200 lb (1,450 kg). Pegasus 2 decayed 3 November 1979. Apollo BP-16 decayed 8 July 1989. | |
| SA-10 | July 30, 196513:00:00 | Third Pegasus micrometeoroid satellite. Orbit: 567 x 535 km. Mass: 3,200 lb (1,450 kg). Pegasus 3 decayed 4 August 1969. Apollo BP-9A decayed 22 November 1975. |