A proposed version of the Juno V for lunar and planetary missions used a Titan I ICBM first stage and a Centaur high-energy third stage atop the basic Juno V cluster. Masses, payload estimated.

LEO Payload: 12,500 kg. to: 185 km Orbit. at: 28.0 degrees. Payload: 3,500 kg. to a: Translunar trajectory. Liftoff Thrust: 682,200 kgf. Total Mass: 539,480 kg. Core Diameter: 6.5 m. Total Length: 60.0 m. Flyaway Unit Cost $: 73.80 million. in 1985 unit dollars.

• Stage Number: 1. 1 x Saturn I Gross Mass: 432,681 kg. Empty Mass: 45,267 kg. Thrust (vac): 773,160 kgf. Isp: 289 sec. Burn time: 150 sec. Isp(sl): 255 sec. Diameter: 6.5 m. Span: 6.5 m. Length: 24.5 m. Propellants: Lox/Kerosene No Engines: 8. H-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 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

• 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