Tetrahedral multi-satellite continuous-coverage constellation

Details Tetrahedral multi-satellite continuous-coverage constellation Tetrahedral multi-satellite continuous-coverage constellation

1985-07-19

1989-08-08

Barefoot, Galen

Aeronautics and astronautics

Spacecraft

Spacecraft formation, orbit, or interplanetary path

B64G 110

Patent

active

048545279

ABSTRACT:
An improved, optimized, four-satellite tetrahedral constellation using common period elliptic orbits is disclosed which provides continuous global coverage (i.e., any point on the earth can always maintain line-of-sight visibilty with at least one of the four satellites). The constellation consists of two satellites having perigees in one hemisphere, and two satellites having perigees in the other hemisphere. All satellites have a common period, and positive visibility angles can be maintained down to a constellation (or satellite) period of 27 hours. At higher altitudes (longer periods) both the minimum visibility angles and the mean visibility angles will tend to increase. Replication may be provided by overlaying arrays with convenient offset. The invention is applicable to any celestial body wherein two satellites have two periapses in one hemisphere and the other two satellites have periapses in the other hemisphere.

REFERENCES:
"Navstar" Global Positioning System, Space Navigations Systems Headquarters, Space and Missile Systems Organization, Jun. 22, 1976.
Draim et al, "Satellite Constellation for Optimal Northern Hemisphere Coverage", Ninth DARPA Strategic Space Symp. at Naval Postgraduate School, Monterey, Calif., Oct. 4-7, 1983, unclassified.

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