Boeing study, 1969, for Saturn follow-on. Plug nozzle, single-stage-to-orbit launch vehicle could itself put 1 million pounds payload into orbit. By addition of up to 12 260 inch solid motors up to 3.5 million pounds payload into orbit with a single launch.

Liftoff Thrust: 31,980,770 kgf. Total Mass: 25,132,660 kg. Core Diameter: 21.9 m. Total Length: 94.0 m. Flyaway Unit Cost $: 1,339.80 million. in 1985 unit dollars.

• Stage Number: 0. 12 x 260 inch solid FL Gross Mass: 1,648,355 kg. Empty Mass: 156,126 kg. Thrust (vac): 3,608,918 kgf. Isp: 263 sec. Burn time: 114 sec. Isp(sl): 238 sec. Diameter: 6.6 m. Span: 6.6 m. Length: 30.5 m. Propellants: Solid No Engines: 1. AJ-260X

• Stage Number: 1. 1 x MLLV Gross Mass: 5,352,400 kg. Empty Mass: 317,400 kg. Thrust (vac): 7,257,500 kgf. Isp: 455 sec. Burn time: 310 sec. Isp(sl): 367 sec. Diameter: 21.9 m. Span: 21.9 m. Length: 78.6 m. Propellants: Lox/LH2 No Engines: 12. CD Module

• 267 - Cohan, Christopher J, Space Transportation Systems, 1980-2000, American Institute of Aeronautics and Astronautics, New York, 1978.