Saturn B-1

American orbital launch vehicle. Most powerful version of Saturn I considered. New low energy second stage with four H-1 engines, S-IV third stage, Centaur fourth stage. Masses, payload estimated.

LEO Payload: 13,000 kg (28,000 lb) to a 185 km orbit at 28.00 degrees. Payload: 4,000 kg (8,800 lb) to a translunar trajectory. Flyaway Unit Cost 1985$: 107.300 million.

Stage Data - Saturn B-1

• Stage 1. 1 x 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. 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). Propellants: Lox/Kerosene. No Engines: 8. Engine: H-1b. Status: Out of Production.

• Stage 2. 1 x Titan Cluster. Gross Mass: 150,000 kg (330,000 lb). Empty Mass: 10,000 kg (22,000 lb). Thrust (vac): 2,940.000 kN (660,930 lbf). Isp: 130 sec. Burn time: 137 sec. Isp(sl): 256 sec. Diameter: 6.10 m (20.00 ft). Span: 6.10 m (20.00 ft). Length: 16.00 m (52.00 ft). Propellants: Lox/Kerosene. No Engines: 4. Engine: LR-89-5. Status: Study 1959. Comments: Masses estimated (cluster of four Titan I first stages).

• Stage 3. 1 x 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. Diameter: 5.49 m (18.01 ft). Span: 5.49 m (18.01 ft). Length: 12.19 m (39.99 ft). Propellants: Lox/LH2. No Engines: 6. Engine: RL-10. Status: Out of Production.

• Stage 4. 1 x Centaur C. Gross Mass: 15,600 kg (34,300 lb). Empty Mass: 1,996 kg (4,400 lb). Thrust (vac): 133.448 kN (30,000 lbf). Isp: 425 sec. Burn time: 430 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 9.14 m (29.98 ft). Propellants: Lox/LH2. No Engines: 2. Engine: RL-10A-1. Status: Out of Production.