|
VTOVL orbital launch vehicle. Year: 1969. Family: VTOVL. Country: USA. Status: Study 1969. 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. Manufacturer: Boeing. Liftoff Thrust: 313,624.200 kN (70,505,525 lbf). Total Mass: 25,132,660 kg (55,408,030 lb). Core Diameter: 21.86 m (71.71 ft). Total Length: 94.00 m (308.00 ft). Flyaway Unit Cost $: 1,339.800 million. in: 1985 unit dollars.
Stage Data - MLLV - Stage Number: 0. 12 x Stage: 260 inch solid FL. Gross Mass: 1,648,355 kg (3,634,000 lb). Empty Mass: 156,126 kg (344,198 lb). Thrust (vac): 35,391.395 kN (7,956,302 lbf). Isp: 263 sec. Burn time: 114 sec. Isp(sl): 238 sec. Diameter: 6.60 m (21.60 ft). Span: 6.60 m (21.60 ft). Length: 30.48 m (99.99 ft). Propellants: Solid. No Engines: 1. Engine: AJ-260X. Status: Study 1967. 260 inch solid booster - full length. These would have been the flight configuration motors, replacing the Saturn V first stage or being used as booster motors in various Uprated Saturn and Nova configurations.
- Stage Number: 1. 1 x Stage: MLLV. Gross Mass: 5,352,400 kg (11,800,000 lb). Empty Mass: 317,400 kg (699,700 lb). Thrust (vac): 71,171.700 kN (16,000,035 lbf). Isp: 455 sec. Burn time: 310 sec. Isp(sl): 367 sec. Diameter: 21.86 m (71.71 ft). Span: 21.86 m (71.71 ft). Length: 78.63 m (257.97 ft). Propellants: Lox/LH2. No Engines: 12. Engine: CD Module. Status: Study 1969. Boeing study, 1969.
Bibliography and Further Reading - Cohan, Christopher J, Space Transportation Systems, 1980-2000, American Institute of Aeronautics and Astronautics, New York, 1978.
|