| Saturn II | |||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||
| Country-Origin: | United States | ||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||
| Function: | Orbital launch vehicle | ||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||
| Manufacturer: | North American (S-II) Douglas (S-IVB) | ||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||
| Height: | 167feet | ||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||
| Diameter: | 33feet | ||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||
| Mass: | 1112000lb4178200lb | ||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||
| Stages: | 2 | ||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||
| Capacities: |
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| Status: | Study 1966 | ||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||
| Sites: | Kennedy Space Center Launch Complex 39, | ||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||
| Launches: | 0 | ||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||
| Family: | Saturn | ||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||
| Stagedata: |
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The Saturn II was a series of American expendable launch vehicles, studied by North American Aviation under a NASA contract in 1966, derived from the Saturn V rocket used for the Apollo lunar program.[4] The intent of the study was to eliminate production of the Saturn IB, and create a lower-cost heavy launch vehicle based on Saturn V hardware. North American studied three versions with the S-IC first stage removed: the INT-17, a two-stage vehicle with a low Earth orbit payload capability of 47000lb; the INT-18, which added Titan UA1204 or UA1207 strap-on solid rocket boosters, with payloads ranging from 47000lb to 146400lb; and the INT-19, using solid boosters derived from the Minuteman missile first stage.
For this study, the Boeing company also investigated configurations designated INT-20 and INT-21 which employed its S-IC first stage, and eliminated either North American's S-II second stage, or the Douglas S-IVB third stage. Budget constraints led to cancellation of the study and exclusive use of the Space Shuttle for orbital payloads.
There was a large payload gap between the Saturn IB's 46000lb low Earth orbit capacity and the Saturn V's 310000lb capability. In the mid-1960s NASA's Marshall Space Flight Center (MSFC) initiated several studies to extend the capabilities of the Saturn family. NASA specified a LEO of 185km (115miles), 28° inclination for payload calculations, and the studies examined a number of Modified Launch Vehicle (MLV) configurations based on the Saturn IB and Saturn V launch vehicles as well as Intermediate Payload (INT) launch vehicles based on modified Saturn V stages (MS-IC, MS-II, and MS-IVB). Martin Marietta (builder of Atlas and Titan rockets), Boeing (builder of S-IC first stages), and North American Aviation (builder of the S-II second stage) were three of the companies that provided responses.
North American believed the best way to fill the gap was to use the Saturn V's second stage, the S-II, as the first stage of an intermediate launch vehicle. The basic concept of the Saturn II was to save money by ceasing production of the Saturn IB rocket, and replacing it with launch vehicles built entirely with current Saturn V components. This would allow closing down Chrysler Space Division production lines for the S-IB first stage, and would allow for more efficient integration of rocket systems.
The baseline for the Saturn II was a Saturn V, without the Boeing-built S-IC first stage. The Saturn V's second stage S-II became the first stage, and the non-restartable S-IVB-200 used on the Saturn IB became the second stage. Such a vehicle could not fly without modification, because the S-II was designed to operate in the near-vacuum of high altitude space. Atmospheric thrust suppression reduced the five Rocketdyne J-2 engines' 1000000lbf of vacuum thrust to 546500lbf at sea level,[5] insufficient to lift the 1364900lb weight of the two stages off of the ground, even without a payload. This required that the S-II be either refit with higher thrust engines, augmented with solid rocket boosters, or both. Another design variable was the amount of the full 1005500lb propellant load carried in the S-II, and 241300lb in the S-IVB stage.
Before any version could be put into production, work on all Saturn variants was stopped in favor of launching all future payloads from the Space Shuttle.
The Saturn INT-17 was the first version of the Saturn II to be considered. It replaced the first stage's five J-2 engines with seven higher thrust HG-3-SL engines, giving 1334000lbf of sea level thrust. It would burn a reduced S-II propellant load of 986000lb in 200 seconds. The vehicle had a LEO payload capability of 92000lb with a gross weight of 1112000lb. The reduced payload permitted a savings of 300kg (700lb) in structural weight, and omitting the S-IVB restart capability saved 700kg (1,500lb).[6]
This configuration was dropped when it was determined that the HG-3-SL could not compete with the J-2 in terms of overall performance, reliability, and cost-effectiveness.[6] This required the addition of booster stages in order to provide more takeoff thrust.
The Saturn INT-18 would have used the standard S-II with J-2 engines, augmented by two or four Titan SRBs. The UA1204 and UA1207 boosters were considered, with the highest total impulse configuration using four UA1207 boosters, capable of placing 146000lb of payload into low Earth orbit. Designers considered changing the amount of fuel loaded into the rocket, and whether to ignite the S-II stage on the ground, or whether to launch using the solids, and start the main stage in flight. Two versions omitted the S-IVB stage.
The following configurations were studied:[7]
| Liftoff Mass | Boosters | S-II propellant | S-IVB propellant | Payload | |
|---|---|---|---|---|---|
| 1132000abbr=onNaNabbr=on | 4 UA1204 | 215400abbr=onNaNabbr=on | 80300abbr=onNaNabbr=on | 21300abbr=onNaNabbr=on | |
| 1132000abbr=onNaNabbr=on | 4 UA1204 | 215400abbr=onNaNabbr=on | 78500abbr=onNaNabbr=on | 23100abbr=onNaNabbr=on | |
| 1030400abbr=onNaNabbr=on | 2 UA1207 | 254000abbr=onNaNabbr=on | 80700abbr=onNaNabbr=on | 27400abbr=onNaNabbr=on | |
| 1132400abbr=onNaNabbr=on | 2 UA1207 | 349200abbr=onNaNabbr=on | 79800abbr=onNaNabbr=on | 35400abbr=onNaNabbr=on | |
| 1083000abbr=onNaNabbr=on | 2 UA1205 | 431600abbr=onNaNabbr=on | 77400abbr=onNaNabbr=on | 40500abbr=onNaNabbr=on | |
| 1570500abbr=onNaNabbr=on | 4 UA1205 | 440400abbr=onNaNabbr=on | 77400abbr=onNaNabbr=on | 51700abbr=onNaNabbr=on | |
| 1895200abbr=onNaNabbr=on | 4 UA1207 | 446700abbr=onNaNabbr=on | 75700abbr=onNaNabbr=on | 66400abbr=onNaNabbr=on | |
| 1476200abbr=onNaNabbr=on | 4 UA1205 | 446700abbr=onNaNabbr=on | No S-IVB | 39000abbr=onNaNabbr=on | |
| 1779600abbr=onNaNabbr=on | 4 UA1207 | 446700abbr=onNaNabbr=on | No S-IVB | 44000abbr=onNaNabbr=on |
The Saturn INT-19 would have used smaller solid boosters, derived from the first stage of the Minuteman missile, to supplement the thrust of the S-II. Eleven configurations were studied, using between four and twelve solids, with some being started at lift-off, and some being started in flight, and varying propellant loads in the Saturn stages. The S-II stage would have been modified by refitting the J-2–SL engines with reduced expansion ratio nozzles, to increase sea level thrust to 174400lbf per engine. The highest total impulse configuration would have used twelve boosters, with eight started at launch and four started after the first group had been jettisoned. It would have been capable of lofting a payload of 34200kg (75,400lb).
The following configurations were studied:[8]
| Liftoff mass | Boosters, liftoff | Boosters, round 1 | Boosters, round 2 | S-II propellant | S-IVB propellant | Payload | |
|---|---|---|---|---|---|---|---|
| 328300kg (723,800lb) | 0 | 0 | 0 | 188200kg (414,900lb) | 77100kg (170,000lb) | 5500kg (12,100lb) | |
| 463500kg (1,021,800lb) | 2 | 2 | 0 | 217700kg (479,900lb) | 80300kg (177,000lb) | 13200kg (29,100lb) | |
| 579600kg (1,277,800lb) | 4 | 2 | 0 | 277600kg (612,000lb) | 76600kg (168,900lb) | 20100kg (44,300lb) | |
| 579600kg (1,277,800lb) | 4 | 4 | 0 | 236700kg (521,800lb) | 73000kg (161,000lb) | 18100kg (39,900lb) | |
| 722900kg (1,593,700lb) | 6 | 2 | 0 | 367800kg (810,900lb) | 76600kg (168,900lb) | 27200kg (60,000lb) | |
| 722900kg (1,593,700lb) | 6 | 4 | 0 | 318400kg (702,000lb) | 78000kg (172,000lb) | 26800kg (59,100lb) | |
| 734200kg (1,618,600lb) | 6 | 4 | 2 | 294800kg (649,900lb) | 81200kg (179,000lb) | 23100kg (50,900lb) | |
| 722900kg (1,593,700lb) | 6 | 6 | 0 | 273900kg (603,800lb) | 78900kg (173,900lb) | 25400kg (56,000lb) | |
| 866700kg (1,910,700lb) | 8 | 4 | 0 | 410900kg (905,900lb) | 80700kg (177,900lb) | 28800kg (63,500lb) | |
| 866700kg (1,910,700lb) | 8 | 4 | 0 | 410900kg (905,900lb) | 75700kg (166,900lb) | 33700kg (74,300lb) | |
| 866700kg (1,910,700lb) | 8 | 4 | 0 | 410900kg (905,900lb) | 75200kg (165,800lb) | 34200kg (75,400lb) |