Saturn A-2 - Credit: © Mark Wade. 2,624 bytes. 76 x 661 pixels.

More powerful version of Saturn I with low energy second stage consisting of cluster of four IRBM motors and tankage, Centaur third stage. Masses, payload estimated.

LEO Payload: 10,000 kg. to: 185 km Orbit. at: 38.0 degrees. Payload: 2,000 kg. to a: Translunar trajectory. Liftoff Thrust: 743,890 kgf. Total Mass: 702,960 kg. Core Diameter: 6.5 m. Total Length: 62.0 m. Flyaway Unit Cost $: 63.80 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 Jupiter Cluster Gross Mass: 226,716 kg. Empty Mass: 27,205 kg. Thrust (vac): 309,411 kgf. Isp: 282 sec. Burn time: 172 sec. Isp(sl): 248 sec. Diameter: 5.3 m. Span: 5.3 m. Length: 18.3 m. Propellants: Lox/Kerosene No Engines: 4. S-3

• Stage Number: 3. 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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