 | Saturn V 120" SRB
Credit - © Mark Wade
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Orbital launch vehicle. Year: 1965. Family: Saturn V. Country: USA. Status: Study 1965. MSFC study, 1965. 4 Titan UA1205 solid rocket boosters; Saturn IC stretched 337 inches with 6.0 million pounds propellant and 5 F-1 engines; S-II with 970,000 pounds propellant and 5 J-2 engines; S-IVB strengthened but with standard 230,000 lbs propellant, 1 J-2 engine. Manufacturer: Von Braun. LEO Payload: 160,880 kg (354,670 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 57,500 kg (126,700 lb). to a: Translunar trajectory. Liftoff Thrust: 54,920.000 kN (12,346,500 lbf). Total Mass: 4,615,440 kg (10,175,300 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 113.00 m (370.00 ft). Flyaway Unit Cost $: 71.920 million. in: 1985 unit dollars.
Stage Data - Saturn MLV-V-4(S)-A - 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 MS-IC-4(S)B. Gross Mass: 2,875,500 kg (6,339,300 lb). Empty Mass: 154,000 kg (339,000 lb). Thrust (vac): 38,717.600 kN (8,704,063 lbf). Isp: 304 sec. Burn time: 206 sec. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 50.58 m (165.94 ft). Propellants: Lox/Kerosene. No Engines: 5. Engine: F-1. Status: Study 1966. S-IC with 336 inch stretch, 6,000,0000 lbs propellant, structural strength increased from 56% to 65% depending on station, resulting in 13.9% increase in empty weight.
- Stage Number: 2. 1 x Stage: Saturn MS-II-1. Gross Mass: 521,447 kg (1,149,593 lb). Empty Mass: 49,877 kg (109,959 lb). Thrust (vac): 5,165.790 kN (1,161,316 lbf). Isp: 425 sec. Burn time: 361 sec. Isp(sl): 306 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 25.88 m (84.90 ft). Propellants: Lox/LH2. No Engines: 5. Engine: J-2. Status: Study 1965. Basic Saturn II with 41 inch stretch of hydrogen tank.
- 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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