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Model: Saturn I. Gross Mass: 432,681 kg (953,898 lb). Empty Mass: 45,267 kg (99,796 lb). Thrust (vac): 7,582.100 kN (1,704,524 lbf). Isp: 289 sec. Burn time: 150 sec. Propellants: Lox/Kerosene. Isp(sl): 255 sec. Diameter: 6.52 m (21.39 ft). Span: 6.52 m (21.39 ft). Length: 24.48 m (80.31 ft). Country: USA. No Engines: 8. Motor: H-1. Status: Study 1960. Cost $ : 43.500 million. First Flight: 1958. Last Flight: 1965. No Launched: 15.

Configuration as flown, Saturn I.

Model: Saturn IB. Gross Mass: 448,648 kg (989,099 lb). Empty Mass: 41,594 kg (91,699 lb). Thrust (vac): 8,241.763 kN (1,852,822 lbf). Isp: 296 sec. Burn time: 155 sec. Propellants: Lox/Kerosene. Isp(sl): 262 sec. Diameter: 6.52 m (21.39 ft). Span: 6.52 m (21.39 ft). Length: 24.48 m (80.31 ft). Country: USA. No Engines: 8. Motor: H-1b. Status: Study 1965. Cost $ : 43.500 million. First Flight: 1963. Last Flight: 1975. No Launched: 46.

Configuration as flown, Saturn IB.

Model: Saturn S-IB-4. Gross Mass: 1,813,729 kg (3,998,587 lb). Empty Mass: 108,823 kg (239,913 lb). Thrust (vac): 30,962.526 kN (6,960,653 lbf). Isp: 304 sec. Burn time: 155 sec. Propellants: Lox/Kerosene. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 11.28 m (37.00 ft). Length: 28.96 m (95.01 ft). Country: USA. No Engines: 4. Motor: F-1. Status: Study 1960.

Model: Saturn S-IB-2. Gross Mass: 725,491 kg (1,599,433 lb). Empty Mass: 68,014 kg (149,945 lb). Thrust (vac): 13,339.956 kN (2,998,941 lbf). Isp: 304 sec. Burn time: 139 sec. Propellants: Lox/Kerosene. Isp(sl): 265 sec. Diameter: 8.25 m (27.06 ft). Span: 10.00 m (32.00 ft). Length: 34.50 m (113.10 ft). Country: USA. No Engines: 2. Motor: F-1. Status: Study 1960.

Model: Saturn S-IB-A. Gross Mass: 448,600 kg (988,900 lb). Empty Mass: 41,600 kg (91,700 lb). Thrust (vac): 9,045.600 kN (2,033,532 lbf). Isp: 296 sec. Burn time: 128 sec. Propellants: Lox/Kerosene. Isp(sl): 262 sec. Diameter: 6.52 m (21.39 ft). Span: 6.52 m (21.39 ft). Length: 24.48 m (80.31 ft). Country: USA. No Engines: 8. Motor: H-1c. Status: Study 1965.

Douglas Studies, 1965: S-1B with 225 k lbf H-1's

Model: Saturn S-1B-4. Gross Mass: 444,700 kg (980,300 lb). Empty Mass: 37,600 kg (82,800 lb). Thrust (vac): 4,120.700 kN (926,370 lbf). Isp: 296 sec. Burn time: 282 sec. Propellants: Lox/Kerosene. Isp(sl): 262 sec. Diameter: 6.52 m (21.39 ft). Span: 6.52 m (21.39 ft). Length: 24.48 m (80.31 ft). Country: USA. No Engines: 4. Motor: H-1b. Status: Study 1966.

Chrysler Studies, 1966: S-1B with 4 H-1's for use with Titan UA1205 strap-ons

Model: Saturn IB-11. Gross Mass: 505,953 kg (1,115,435 lb). Empty Mass: 48,545 kg (107,023 lb). Thrust (vac): 8,241.763 kN (1,852,822 lbf). Isp: 296 sec. Burn time: 153 sec. Propellants: Lox/Kerosene. Isp(sl): 262 sec. Diameter: 6.52 m (21.39 ft). Span: 6.52 m (21.39 ft). Length: 30.48 m (99.99 ft). Country: USA. No Engines: 8. Motor: H-1b. Status: Study 1966.

20 foot stretch of Saturn IB for use with UA1207 7 segment solid rocket strap-on units.

Model: Saturn IB-15. Gross Mass: 478,103 kg (1,054,036 lb). Empty Mass: 45,873 kg (101,132 lb). Thrust (vac): 8,241.763 kN (1,852,822 lbf). Isp: 296 sec. Burn time: 144 sec. Propellants: Lox/Kerosene. Isp(sl): 262 sec. Diameter: 6.52 m (21.39 ft). Span: 6.52 m (21.39 ft). Length: 27.43 m (89.99 ft). Country: USA. No Engines: 8. Motor: H-1b. Status: Study 1966.

10 foot stretch of Saturn IB. Not found useful in any configuration except with Minuteman first-stage strap-ons to augment thrust.

Model: Saturn S-IC-TLB. Gross Mass: 952,500 kg (2,099,900 lb). Empty Mass: 68,000 kg (149,000 lb). Thrust (vac): 15,532.700 kN (3,491,890 lbf). Isp: 304 sec. Burn time: 167 sec. Propellants: Lox/Kerosene. Isp(sl): 265 sec. Diameter: 6.61 m (21.68 ft). Span: 10.58 m (34.71 ft). Length: 36.36 m (119.29 ft). Country: USA. No Engines: 2. Motor: F-1. Status: Study 1967.

Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): S-IC Technology Liquid Booster: 260 inch liquid booster with 2 x F-1 engines, recoverable/reusable

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