Saturn II home
topic index
Saturn II stage

Credit - © Mark Wade
Model: 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. Propellants: Lox/LH2. 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). Country: USA. No Engines: 5. Motor: J-2. Status: Study 1968. Cost $ : 290.000 million. First Flight: 1967. Last Flight: 1973. No Launched: 24.

Configuration as flown.

Model: Saturn S-II. Gross Mass: 100,000 kg (220,000 lb). Empty Mass: 14,000 kg (30,000 lb). Thrust (vac): 3,557.313 kN (799,716 lbf). Isp: 420 sec. Burn time: 100 sec. Propellants: Lox/LH2. Isp(sl): 300 sec. Diameter: 6.60 m (21.60 ft). Span: 6.60 m (21.60 ft). Length: 22.56 m (74.01 ft). Country: USA. No Engines: 4. Motor: J-2. Status: Study 1960.

Early design version for use with Saturn I first stage.

Model: Saturn S-II-C3. Gross Mass: 204,044 kg (449,840 lb). Empty Mass: 24,938 kg (54,978 lb). Thrust (vac): 3,557.313 kN (799,716 lbf). Isp: 420 sec. Burn time: 200 sec. Propellants: Lox/LH2. Isp(sl): 300 sec. Diameter: 8.25 m (27.06 ft). Span: 8.25 m (27.06 ft). Length: 21.30 m (69.80 ft). Country: USA. No Engines: 4. Motor: J-2. Status: Study 1960.

Version for Saturn C-3.

Model: Saturn S-II-4. Gross Mass: 294,731 kg (649,770 lb). Empty Mass: 24,938 kg (54,978 lb). Thrust (vac): 3,557.313 kN (799,716 lbf). Isp: 420 sec. Burn time: 296 sec. Propellants: Lox/LH2. Isp(sl): 300 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 16.76 m (54.98 ft). Country: USA. No Engines: 4. Motor: J-2. Status: Study 1960.

Version for Saturn C-4.

Model: Saturn S-II-8. Gross Mass: 770,835 kg (1,699,400 lb). Empty Mass: 63,480 kg (139,940 lb). Thrust (vac): 8,265.260 kN (1,858,104 lbf). Isp: 425 sec. Burn time: 338 sec. Propellants: Lox/LH2. Isp(sl): 306 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 42.68 m (140.02 ft). Country: USA. No Engines: 8. Motor: J-2. Status: Study 1960.

Version for Saturn C-8.

Model: Saturn II C-5A. Gross Mass: 384,057 kg (846,700 lb). Empty Mass: 31,740 kg (69,970 lb). Thrust (vac): 4,446.648 kN (999,646 lbf). Isp: 420 sec. Burn time: 320 sec. Propellants: Lox/LH2. Isp(sl): 200 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 21.39 m (70.17 ft). Country: USA. No Engines: 5. Motor: J-2. Status: Study 1961. First Flight: 1961. Last Flight: 1961. No Launched: 1.

Final common second stage design for Saturn C-3, C-4 and C-5 (November 1961). Developed into Saturn V second stage.

Model: 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. Propellants: Lox/LH2. 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). Country: USA. No Engines: 5. Motor: J-2. Status: Study 1965.

Basic Saturn II with 41 inch stretch of hydrogen tank.

Model: Saturn MS-II-1-J-2T-200K. Gross Mass: 521,447 kg (1,149,593 lb). Empty Mass: 49,877 kg (109,959 lb). Thrust (vac): 4,446.648 kN (999,646 lbf). Isp: 435 sec. Burn time: 429 sec. Propellants: Lox/LH2. Isp(sl): 300 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 25.88 m (84.90 ft). Country: USA. No Engines: 5. Motor: J-2T-200K. Status: Study 1965.

Basic Saturn II with 41 inch stretch of hydrogen tank, uprated J-2T 200k engines with 10 second increase in specific impulse.

Model: Saturn II-SL. Gross Mass: 490,952 kg (1,082,363 lb). Empty Mass: 44,240 kg (97,530 lb). Thrust (vac): 5,500.765 kN (1,236,621 lbf). Isp: 390 sec. Burn time: 310 sec. Propellants: Lox/LH2. Isp(sl): 275 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 24.84 m (81.49 ft). Country: USA. No Engines: 5. Motor: J-2-SL. Status: Study 1966.

Saturn II modifed with reduced expansion ratio J-2 engines for use a first stage (sea level launch). Requires solid rocket motor augmentation to get off the ground.

Model: Saturn MS-II-2. Gross Mass: 600,788 kg (1,324,510 lb). Empty Mass: 59,844 kg (131,933 lb). Thrust (vac): 7,003.477 kN (1,574,444 lbf). Isp: 451 sec. Burn time: 324 sec. Propellants: Lox/LH2. Isp(sl): 280 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 29.59 m (97.08 ft). Country: USA. No Engines: 5. Motor: HG-3. Status: Study 1966.

Basic Saturn II with 187 inch stretch of propellant tanks and high chamber pressure SSME-type engines with 65% increase in thrust and 26 second improvement in specific impulse.

Model: Saturn MS-II-1A. Gross Mass: 600,800 kg (1,324,500 lb). Empty Mass: 60,000 kg (132,000 lb). Thrust (vac): 6,380.941 kN (1,434,493 lbf). Isp: 421 sec. Burn time: 345 sec. Propellants: Lox/LH2. Isp(sl): 200 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 29.59 m (97.08 ft). Country: USA. No Engines: 7. Motor: J-2. Status: Study 1966.

Basic Saturn II with 187 inch stretch of propellant tanks, 1.2 million pound propellant capacity, and 7 J-2 engines.

Model: Saturn II-INT-17. Gross Mass: 495,000 kg (1,091,000 lb). Empty Mass: 48,000 kg (105,000 lb). Thrust (vac): 9,713.400 kN (2,183,659 lbf). Isp: 450 sec. Burn time: 200 sec. Propellants: Lox/LH2. Isp(sl): 275 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 24.84 m (81.49 ft). Country: USA. No Engines: 7. Motor: HG-3-SL. Status: Study 1966.

Saturn II modifed with reduced expansion ratio HG-3 high pressure engines for use a first stage (sea level launch).

Model: Saturn MS-II-1-J-2T-250K. Gross Mass: 521,447 kg (1,149,593 lb). Empty Mass: 49,877 kg (109,959 lb). Thrust (vac): 5,558.310 kN (1,249,558 lbf). Isp: 441 sec. Burn time: 348 sec. Propellants: Lox/LH2. Isp(sl): 290 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 25.88 m (84.90 ft). Country: USA. No Engines: 5. Motor: J-2T-250K. Status: Study 1967.

Basic Saturn II with 41 inch stretch of hydrogen tank, uprated J-2T 250k engines with 25% improvement in thrust and 16 second increase in specific impulse.

Model: Saturn MS-II-3B. Gross Mass: 643,200 kg (1,418,000 lb). Empty Mass: 53,500 kg (117,900 lb). Thrust (vac): 12,455.400 kN (2,800,085 lbf). Isp: 447 sec. Burn time: 204 sec. Propellants: Lox/LH2. Isp(sl): 200 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 29.56 m (96.98 ft). Country: USA. No Engines: 5. Motor: Toroidal 400k. Status: Study 1967.

S-II with 15.5 foot stretch, 1.29 million pounds propellant, 7 x 400,000 lb thrust toroidal engines.

Model: 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. Propellants: Lox/LH2. 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). Country: USA. No Engines: 5. Motor: 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.

Used on Launch Vehicles:
Contact us with any corrections, additions, or comments.
Conditions for use of drawings, pictures, or other materials from this site..
To contact astronauts or cosmonauts.

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