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Credit - © Mark Wade
Model: Saturn IV. Gross Mass: 50,576 kg (111,500 lb). Empty Mass: 5,217 kg (11,501 lb). Thrust (vac): 400.346 kN (90,001 lbf). Isp: 410 sec. Burn time: 482 sec. Propellants: Lox/LH2. Diameter: 5.49 m (18.01 ft). Span: 5.49 m (18.01 ft). Length: 12.19 m (39.99 ft). Country: USA. No Engines: 6. Motor: RL-10. Status: Study 1960. Cost $ : 43.500 million. First Flight: 1961. Last Flight: 1965. No Launched: 13.

Configuration as flown.

Model: 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. Propellants: Lox/LH2. 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). Country: USA. No Engines: 1. Motor: J-2. Status: Study 1967. First Flight: 1963. Last Flight: 1975. No Launched: 70.

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).

Model: Saturn IVB. Gross Mass: 119,920 kg (264,370 lb). Empty Mass: 13,311 kg (29,345 lb). Thrust (vac): 1,031.983 kN (231,999 lbf). Isp: 425 sec. Burn time: 475 sec. Propellants: Lox/LH2. 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). Country: USA. No Engines: 1. Motor: J-2. Status: Study 1960. Cost $ : 58.290 million.

Configuration as flown on Saturn V.

Model: Saturn IVB (S-V). Gross Mass: 119,900 kg (264,300 lb). Empty Mass: 13,300 kg (29,300 lb). Thrust (vac): 1,031.600 kN (231,913 lbf). Isp: 421 sec. Burn time: 475 sec. Propellants: Lox/LH2. 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). Country: USA. No Engines: 1. Motor: J-2. Status: Study 1968. First Flight: 1967. Last Flight: 1973. No Launched: 13.

Saturn V version of S-IVB stage for use with upper stage.

Model: Saturn IVB C-3B. Gross Mass: 52,144 kg (114,957 lb). Empty Mass: 6,801 kg (14,993 lb). Thrust (vac): 889.325 kN (199,928 lbf). Isp: 420 sec. Burn time: 207 sec. Propellants: Lox/LH2. Isp(sl): 200 sec. Diameter: 5.59 m (18.33 ft). Span: 5.59 m (18.33 ft). Length: 15.40 m (50.50 ft). Country: USA. No Engines: 1. Motor: J-2. Status: Study 1961.

Final common third stage design for Saturn C-3B (November 1961).

Model: Saturn IVB C-5A. Gross Mass: 102,249 kg (225,420 lb). Empty Mass: 11,563 kg (25,492 lb). Thrust (vac): 889.325 kN (199,928 lbf). Isp: 420 sec. Burn time: 415 sec. Propellants: Lox/LH2. Isp(sl): 200 sec. Diameter: 5.59 m (18.33 ft). Span: 5.59 m (18.33 ft). Length: 19.00 m (62.00 ft). Country: USA. No Engines: 1. Motor: J-2. Status: Study 1961. First Flight: 1961. Last Flight: 1961. No Launched: 1.

Final common third stage design for Saturn C-4 and C-5 (November 1961). Developed into Saturn V second stage. After development started, decision taken to boost performance by increasing diameter to 6.61 m and increasing propellant load.

Model: Saturn S-IVC. Gross Mass: 204,044 kg (449,840 lb). Empty Mass: 22,671 kg (49,980 lb). Thrust (vac): 1,031.983 kN (231,999 lbf). Isp: 425 sec. Burn time: 695 sec. Propellants: Lox/LH2. Isp(sl): 306 sec. Diameter: 6.61 m (21.68 ft). Span: 6.61 m (21.68 ft). Length: 22.86 m (74.99 ft). Country: USA. No Engines: 1. Motor: J-2. Status: Study NASA February 1962.

Model: Saturn IVB-A. Gross Mass: 118,800 kg (261,900 lb). Empty Mass: 12,900 kg (28,400 lb). Thrust (vac): 956.100 kN (214,940 lbf). Isp: 421 sec. Burn time: 450 sec. Propellants: Lox/LH2. 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). Country: USA. No Engines: 1. Motor: J-2. Status: Study 1965.

Douglas Studies, 1965: S-IVB with 215k lbf J-1 (actual final model had 230k J-1)

Model: Saturn MS-IVB-x. Gross Mass: 195,000 kg (429,000 lb). Empty Mass: 36,300 kg (80,000 lb). Thrust (vac): 912.000 kN (205,025 lbf). Isp: 421 sec. Burn time: 707 sec. Propellants: Lox/LH2. 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). Country: USA. No Engines: 1. Motor: J-2. Status: Study 1965.

Marshall studies, 1965: S-IVB structurally strengthened to handle larger payloads, otherwise unchanged

Model: 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. Propellants: Lox/LH2. 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). Country: USA. No Engines: 1. Motor: J-2. Status: Study 1965.

Marshall studies, 1965: S-IVB structurally strengthened to handle larger payloads, otherwise unchanged

Model: Saturn MS-IVB-4(S)B. Gross Mass: 118,400 kg (261,000 lb). Empty Mass: 14,100 kg (31,000 lb). Thrust (vac): 1,031.600 kN (231,913 lbf). Isp: 421 sec. Burn time: 411 sec. Propellants: Lox/LH2. Isp(sl): 200 sec. Diameter: 6.61 m (21.68 ft). Span: 6.61 m (21.68 ft). Length: 17.79 m (58.36 ft). Country: USA. No Engines: 1. Motor: J-2. Status: Study Boeing 1967.

Standard S-IVB but with structural strength increased from 78% to 217% depending on station, resulting in 11.8% increase in empty weight.

Model: Saturn MS-IVB-1A. Gross Mass: 179,200 kg (395,000 lb). Empty Mass: 20,400 kg (44,900 lb). Thrust (vac): 1,031.600 kN (231,913 lbf). Isp: 421 sec. Burn time: 625 sec. Propellants: Lox/LH2. Isp(sl): 200 sec. Diameter: 6.61 m (21.68 ft). Span: 6.61 m (21.68 ft). Length: 22.82 m (74.86 ft). Country: USA. No Engines: 1. Motor: J-2. Status: Study 1967.

S-IVB with 16.5 foot stretch, 350,000 pounds propellant, standard J-2 engine.

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© Mark Wade, 1997 - 2008 except where otherwise noted.