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Orbital launch vehicle. Year: 1966. Family: Saturn II. Country: USA. Status: Study 1966. North American study, 1966. Saturn variant with Titan UA1205 or 1207 motors as boosters, Saturn II stage as core, and Saturn IVB upper stage. Various combinations of numbers of strap-ons, propellant loading of the two core stages, and sea-level versus altitude ignition were studied.
| Liftoff Mass - kg | Strapon
Motor Type | Number of Strapons | S-II Propellant - kg | S-IVB Propellant
- kg | Payload - kg |
| 1,132,000 | Titan UA1204 | 4 | 215,400 | 80,300 | 21,300 |
| 1,132,000 | Titan UA1204 | 4 | 215,400 | 78,500 | 23,100 |
| 1,030,400 | Titan UA1207 | 2 | 254,000 | 80,700 | 27,400 |
| 1,132,400 | Titan UA1207 | 2 | 349,200 | 79,800 | 35,400 |
| 1,083,000 | Titan UA1205 | 2 | 431,600 | 77,400 | 40,500 |
| 1,570,500 | Titan UA1205 | 4 | 440,400 | 74,400 | 51,700 |
| 1,895,200 | Titan UA1207 | 4 | 446,700 | 75,700 | 66,400 |
| 1,476,200 | Titan UA1205 | 4 | 446,700 | No
S-IVB | 39,000 |
| 1,779,600 | Titan UA1207 | 4 | 446,700 | No
S-IVB | 44,000 |
Manufacturer: Von Braun. LEO Payload: 66,590 kg (146,800 lb). to: 185 km Orbit. at: 28.00 degrees. Liftoff Thrust: 25,642.100 kN (5,764,573 lbf). Total Mass: 1,966,810 kg (4,336,070 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 51.00 m (167.00 ft). Flyaway Unit Cost $: 387.440 million. in: 1985 unit dollars.
Stage Data - Saturn INT-18 - Stage Number: 0. 4 x Stage: Titan UA1207 . Gross Mass: 319,330 kg (704,000 lb). Empty Mass: 51,230 kg (112,940 lb). Thrust (vac): 7,116.999 kN (1,599,965 lbf). Isp: 272 sec. Burn time: 120 sec. Isp(sl): 245 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 34.14 m (112.00 ft). Propellants: Solid. No Engines: 1. Engine: UA1207.
- Stage Number: 1. 1 x Stage: Saturn II. Gross Mass: 490,778 kg (1,081,980 lb). Empty Mass: 39,048 kg (86,086 lb). Thrust (vac): 5,165.790 kN (1,161,316 lbf). Isp: 421 sec. Burn time: 390 sec. Isp(sl): 200 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 24.84 m (81.49 ft). Propellants: Lox/LH2. No Engines: 5. Engine: J-2.
- Stage Number: 2. 1 x Stage: Saturn IVB (S-IB). Gross Mass: 118,800 kg (261,900 lb). Empty Mass: 12,900 kg (28,400 lb). Thrust (vac): 1,031.600 kN (231,913 lbf). Isp: 421 sec. Burn time: 475 sec. Isp(sl): 200 sec. Diameter: 6.61 m (21.68 ft). Span: 6.61 m (21.68 ft). Length: 17.80 m (58.30 ft). Propellants: Lox/LH2. No Engines: 1. Engine: J-2. Saturn IB version of S-IVB stage. Due to lower payload payload, 300 kg saving in structure compared to Saturn V version. Due to deletion of restart requirement, 700 kg saving in propulsion system (primarily reduction in helium for restart).
Bibliography and Further Reading - Lowther, Scott, Saturn: Development, Details, Derivatives and Descendants, Work in progress. Availabe chapters may be ordered directly from Scott Lowther at web site indicated. Accessed at: http://www.webcreations.com/ptm.
- Alexander, George, Aviation Week and Space Technology, "Manned Flight Planning Gap Delays Saturn Development", 1966-08-08, page 60.
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