Saturn B-1 - Credit: © Mark Wade. 3,470 bytes. 76 x 762 pixels.

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. to: 185 km Orbit. at: 28.0 degrees. Payload: 4,000 kg. to a: Translunar trajectory. Liftoff Thrust: 743,890 kgf. Total Mass: 680,420 kg. Core Diameter: 6.5 m. Total Length: 74.0 m. Flyaway Unit Cost $: 107.30 million. in 1985 unit dollars.

• Stage Number: 1. 1 x Saturn IB Gross Mass: 448,648 kg. Empty Mass: 41,594 kg. Thrust (vac): 840,426 kgf. Isp: 296 sec. Burn time: 155 sec. Isp(sl): 262 sec. Diameter: 6.5 m. Span: 6.5 m. Length: 24.5 m. Propellants: Lox/Kerosene No Engines: 8. H-1b

• Stage Number: 2. 1 x Titan Cluster Gross Mass: 150,000 kg. Empty Mass: 10,000 kg. Thrust (vac): 300,000 kgf. Isp: 130 sec. Burn time: 137 sec. Isp(sl): 256 sec. Diameter: 6.1 m. Span: 6.1 m. Length: 16.0 m. Propellants: Lox/Kerosene No Engines: 4. LR-89-5

• Stage Number: 3. 1 x Saturn IV Gross Mass: 50,576 kg. Empty Mass: 5,217 kg. Thrust (vac): 40,824 kgf. Isp: 410 sec. Burn time: 482 sec. Diameter: 5.5 m. Span: 5.5 m. Length: 12.2 m. Propellants: Lox/LH2 No Engines: 6. RL-10

• Stage Number: 4. 1 x Centaur C Gross Mass: 15,600 kg. Empty Mass: 1,996 kg. Thrust (vac): 13,608 kgf. Isp: 425 sec. Burn time: 430 sec. Isp(sl): 0 sec. Diameter: 3.1 m. Span: 3.1 m. Length: 9.1 m. Propellants: Lox/LH2 No Engines: 2. RL-10A-1

• 45 - Koelle, Heinz Hermann,, Handbook of Astronautical Engineering, McGraw-Hill,New York, 1961.
• 222 - Bilstein, Roger E, Stages to Saturn, US Government Printing Office, 1980.
• 228 - Lowther, Scott, Saturn: Development, Details, Derivatives and Descendants, Work in progress. Availabe chapters may be ordered directly from Scott Lowther at web site indicated. HTML when accessed: http://www.webcreations.com/ptm

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Saturn A-1 to C-5 Credit: © Mark Wade. 12,176 bytes. 639 x 461 pixels.

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