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Saturn V/4-260
Part of Saturn V
American orbital launch vehicle. Boeing study, 1967-1968. Use of full length 260 inch solid rocket boosters with stretched Saturn IC stages presented problems, since the top of the motors came about half way up the liquid oxygen tank of the stage, making transmission of loads from the motors to the core vehicle complex and adding a great deal of weight to the S-IC. Boeing's solution was to retain the standard length Saturn IC, with the 260 inch motors ending half way up the S-IC/S-II interstage, but to provide additional propellant for the S-IC by putting propellant tanks above the 260 inch boosters. These would be drained first and jettisoned with the boosters. This added to the plumbing complexity but solved the loads problem.

Status: Study 1967. Payload: 362,700 kg (799,600 lb). Thrust: 161,859.30 kN (36,387,418 lbf). Gross mass: 10,351,050 kg (22,820,150 lb). Height: 86.00 m (282.00 ft). Diameter: 10.06 m (33.00 ft). Apogee: 185 km (114 mi).

LEO Payload: 362,700 kg (799,600 lb) to a 185 km orbit at 28.00 degrees. Flyaway Unit Cost 1985$: 446.600 million.

Stage Data - Saturn V/4-260



Family: orbital launch vehicle. People: von Braun. Country: USA. Engines: HG-3. Stages: Saturn MS-II-2, AJ-260X, Saturn MS-IC/260.

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