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DAC Helios ISI
Part of DAC Helios
American nuclear-powered orbital launch vehicle. As the basic design, but featuring an Improved Specific Impulse chemical stage that used many engines feeding into single large nozzle.

Status: Study 1963. Payload: 454,500 kg (1,002,000 lb). Thrust: 39,955.80 kN (8,982,421 lbf). Gross mass: 2,948,400 kg (6,500,100 lb). Height: 60.00 m (196.00 ft). Diameter: 24.40 m (80.00 ft). Apogee: 325 km (201 mi).

LEO Payload: 454,500 kg (1,002,000 lb) to a 325 km orbit. Flyaway Unit Cost 1985$: 105.700 million.

Stage Data - DAC Helios ISI



Family: nuclear-powered, orbital launch vehicle. Country: USA. Engines: Chamber/single nozzle, NERVA 1mlbf. Stages: DAC Helios ISI-1, DAC Helios ISI-2. Agency: Douglas.

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