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Global Communications Satellite Using Nuclear Power

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Status: Study 1963. Gross mass: 16,000 kg (35,000 lb). Height: 25.00 m (82.00 ft). Span: 5.00 m (16.40 ft).

The spacecraft, 25 m long, would have the form of a long cone followed by cylindrical sections. The cone would be the nuclear reactor; the conical section contained the communications equipment, on-board control systems, and cylindrical heat radiators for the reactor.

The orientation system would point the satellite to within 0.5 to 1 degrees accuracy. Three such satellites would provide global coverage. Average operating life was expected to be two to three years. In support of this project research was undertaken on a fast-neutron reactor with beryllium reflectors and a niobium case. Coolant cycle would use liquid lithium Li - Li-7. Thermal output of the reactor would be 6,000 kW and net average electrical output 600 kW. The reactor core had a diameter of 0.75 m, a length of 1.1 m, and a mass of 1,000 kg. The draft project of 1963 foresaw completion of system design in 1965 and flights from 1967. Although work continued throughout the 1960's on development of the reactor, the communications satellite itself was not approved.

Electric System: 600.00 average kW.