 | S-1C details
Credit - © Mark Wade
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Orbital launch vehicle. Year: 1965. Family: Saturn V. Country: USA. Status: Study 1965. MSFC study, 1965. Saturn V core, strengthened but not stretched, with 4 Titan UA1205 strap-on solid rocket boosters. Manufacturer: Von Braun. LEO Payload: 118,000 kg (260,000 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 52,900 kg (116,600 lb). to a: Translunar trajectory. Liftoff Thrust: 54,911.500 kN (12,344,596 lbf). Total Mass: 3,947,350 kg (8,702,410 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 102.00 m (334.00 ft). Flyaway Unit Cost $: 463.420 million. in: 1985 unit dollars.
Stage Data - Saturn MLV-V-4(S) - Stage Number: 0. 4 x Stage: Titan UA1205 . Gross Mass: 226,233 kg (498,758 lb). Empty Mass: 33,798 kg (74,511 lb). Thrust (vac): 5,849.411 kN (1,315,000 lbf). Isp: 263 sec. Burn time: 115 sec. Isp(sl): 238 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 25.91 m (85.00 ft). Propellants: Solid. No Engines: 1. Engine: UA1205. Status: Out of production.
- Stage Number: 1. 1 x Stage: Saturn IC. Gross Mass: 2,286,217 kg (5,040,245 lb). Empty Mass: 135,218 kg (298,104 lb). Thrust (vac): 38,703.160 kN (8,700,816 lbf). Isp: 304 sec. Burn time: 161 sec. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 42.06 m (137.99 ft). Propellants: Lox/Kerosene. No Engines: 5. Engine: F-1.
- Stage Number: 2. 1 x Stage: Saturn MS-II-4(S)B. Gross Mass: 494,100 kg (1,089,300 lb). Empty Mass: 42,300 kg (93,200 lb). Thrust (vac): 5,169.000 kN (1,162,037 lbf). Isp: 421 sec. Burn time: 355 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. Status: Study 1968. Standard S-II but with structural strength increased from 86% to 502% depending on station, resulting in 8.6% increase in empty weight.
- Stage Number: 3. 1 x Stage: Saturn MS-IVB-1. Gross Mass: 120,500 kg (265,600 lb). Empty Mass: 13,900 kg (30,600 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: 18.08 m (59.31 ft). Propellants: Lox/LH2. No Engines: 1. Engine: J-2. Status: Study 1965. Marshall studies, 1965: S-IVB structurally strengthened to handle larger payloads, otherwise unchanged
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.
- Saturn V Improvement Study, Final report, NASA Contract NAS8-11359.
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