E-1 Engine - Credit: © Mark Wade. 18,356 bytes. 437 x 341 pixels.

The very first design that would lead to Saturn. A 1.5 million pound thrust booster using four E-1 engines - initial consideration of using a single USAF F-1 engine abandoned because of development time. Existing ICBM tankage clustered above the engines.

LEO Payload: 11,000 kg. to: 185 km Orbit. at: 28.0 degrees. Liftoff Thrust: 689,180 kgf. Total Mass: 572,840 kg. Core Diameter: 9.2 m. Total Length: 60.0 m. Flyaway Unit Cost $: 14.00 million. in 1985 unit dollars.

• Stage Number: 1. 1 x Super-Jupiter Gross Mass: 454,500 kg. Empty Mass: 45,400 kg. Thrust (vac): 768,700 kgf. Isp: 290 sec. Burn time: 150 sec. Isp(sl): 260 sec. Diameter: 9.2 m. Span: 9.2 m. Length: 24.0 m. Propellants: Lox/Kerosene No Engines: 4. E-1

• Stage Number: 2. 1 x Titan 1-1 Gross Mass: 76,203 kg. Empty Mass: 4,000 kg. Thrust (vac): 149,685 kgf. Isp: 290 sec. Burn time: 138 sec. Isp(sl): 256 sec. Diameter: 3.1 m. Span: 3.1 m. Length: 16.0 m. Propellants: Lox/Kerosene No Engines: 2. LR-87-3

• Stage Number: 3. 1 x Titan 1-2 Gross Mass: 28,939 kg. Empty Mass: 1,725 kg. Thrust (vac): 36,288 kgf. Isp: 308 sec. Burn time: 225 sec. Isp(sl): 210 sec. Diameter: 2.3 m. Span: 2.3 m. Length: 9.8 m. Propellants: Lox/Kerosene No Engines: 1. LR-91-3

• 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