Satellite system configuration

Details Satellite system configuration Satellite system configuration

1981-02-11

1983-05-24

Frankfort, Charles E.

Aeronautics and astronautics

Spacecraft

Spacecraft formation, orbit, or interplanetary path

244161, 244173, B64G 100, B64G 164, B64G 144

Patent

active

043846920

ABSTRACT:
A new satellite system configuration is comprised of a power module with rigidly attached solar arrays and a control module including a sun pointing unit, an earth pointing unit and a rotary interface. The power module is attached to one face of the sun pointing unit and an opposite face of the sun pointing unit is attached to the earth pointing unit through the rotary interface to allow the earth pointing unit to remain pointing to the earth while the sun pointing unit rotates relative to it to keep the rigidly attached solar arrays of the power module pointing toward the sun. The earth pointing unit has a docking area for subsequent orbital docking of one or more earth pointing payload satellites to be serviced and controlled by the power and control modules.

REFERENCES:
patent: 3781647 (1973-12-01), Glaser
John Overall, Jr., "25 kw Power Module Evolution Study", Proceedings of 14th Intersociety Energy Conversion Conf., Aug. 1979, pp. 1231-1236.
Bernard Raab, ". . . Dynamic Isotope Power System for Spacecraft", 15th Intersociety Energy Conversion Conf., Aug. 1980, pp. 1020-1025.

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