Tetrahedral multi-satellite continuous-coverage constellation

• US 4,854,527 A
• Filed: 07/19/1985
• Issued: 08/08/1989
• Est. Priority Date: 07/19/1985
• Status: Expired due to Term

• Current Assignee: John E. Draim
• Original Assignee: John E. Draim
• Inventors: Draim, John E.
• Primary Examiner(s): BAREFOOT, GALEN L
• Application Number:
  US06/756,635
• Time in Patent Office: 1,481 Days
• Field of Search: 244/158 R, 455/12, 455/13, 455/98
• US Class Current: 244/158.4
• CPC Class Codes: B64G 1/1007 Communications satellites
• CPC Class Codes: B64G 1/1085 Swarms and constellations
• CPC Class Codes: B64G 1/242 Orbits and trajectories
• CPC Class Codes: H04B 7/195 Non-synchronous stations

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.

Claims

1. A communication system comprising a constellation of inclined elliptic artificial satellites orbiting earth for providing continuous global line-of-sight visibility and having communication means for providing communication via the means of at least one satellite at all times with all points on the earth ;

said constellation comprising four common-period elliptic-orbit satellites, said satellites having orbital parameters of period, inclination angle, eccentricity, right ascension of ascending nodes, arguments of perigee, and mean anomaly relationship, two of said satellites having perigees in one hemisphere and the other two of said satellites having perigees in the other hemisphere, said satellites continuously defining a tetrahedron which completely encloses the earth and whose planes do not intersect the earth'"'"'s surface so as to assure said continuous visibility.

2. The communication system of claim 1 wherein said one hemisphere is the Northern Hemisphere and said other hemisphere is the Southern Hemisphere.

3. The communication system of claim 1 wherein the minimum constellation or satellite period is substantially 27 hours, with no maximum period limitation.

4. The communication system of claims 1, 2 or 3 wherein at least one of said orbital parameters is fixed so as to favor coverage of selected geographical regions on earth while maintaining said continuous global line-of-site visibility, said orbital parameters being inclination angle, eccentricity, right ascensions of ascending nodes, arguments of perigee, and mean anomaly relationship.

5. The communication system of claim 1 wherein the axis of symmetry of said satellite constellation is selected so as to provide a predetermined orientation with respect to the earth.

6. The communication system as in claims 1, 2 or 3, wherein the constellation period may be upwardly adjusted from the minimum value in order to increase the minimum visibility or look angles from earth-bound or space-bound points, to values exceeding a predetermined positive visibility angle criteria greater than zero.

7. The communication system as in claims 1, 2 or 3, wherein any or all of the orbital parameters of inclination angle, eccentricity, right ascensions of ascending nodes, arguments or perigee and mean anomaly relationships are adjusted with predetermined excursions off the optimum for even global coverae, so as to preferentially favor one hemisphere over the other as to minimum visibility or look angles, while always maintaining for both hemisphere complete and continuous coverage or visibility in both hemispheres.

8. The communication system as in claims 1, 2 or 3, wherein the constellation or satellite periods are selectively less than the 27-hour value required for complete global coverage, or wherein the various orbital parameters are adjusted with predetermined excursions off the optimum for the purpose of obtaining selective coverage distributions or critical areas, with the resulting satellite coverage gaps located geographically in selected non-important areas so that said gaps will cause an absence of or a minimization of adverse effect on the performance of the system using the array.

9. The communication system as in claims 1, 2 or 3 further comprising

at least one additional continuous coverage constellation overlaying said first recited constellation with any selected orientation.

10. The communication system as in claims 1, 2 or 3 further comprising additional satellites with the same or similar orbital parameters overlaying said first recited constellation with any selected orientation so as to provide n-tuple redundant continuous coverage.

11. A communication system comprising a constellation of artificial satellites orbiting a celestial body for providing continuous line-of-sight visibility and having communication means for providing communication via the means of at least one satellite at all times with all points on the celestial body ;

said constellation comprising four common period elliptic-orbit satellites, said satellites having orbital parameters of period, inclination angle, eccentricity, right ascension of ascending nodes, arguments of parigee, and mean anomaly relationship, two of said satellites having periapses in one hemisphere of said celestial body and the other two of said satellites having periapses in the other hemisphere of said celestial body, said satellites continuously defining a tetrahedron which completely encloses said celestial body and whose planes do not intersect said celestial body'"'"'s surface so as to assure said continuous visibility.

12. The method of providing a constellation of inclined elliptic artificial satellites for providing continuous global line-of-sight visibility to any point on the earth'"'"'s surface and within the maximum operating radius from the earth'"'"'s center of said satellites;

said method comprising the step of orbiting four common-period elliptic-orbit satellites, said satellites having orbital parameters of period, inclination angle, eccentricity, right ascension of ascending nodes, arguments of perigee, and mean anomaly relationship, two of said satellites having perigees in one hemisphere and the other two of said satellites having perigees in the other hemisphere, said satellites continuously defining a tetrahedron which completely encloses the earth and whose planes do not intersect the earth'"'"'s surface so as to assure said continuous visibility.

13. The satellite constellation of claim 12 wherein at least one of said orbital parameters is fixed so as to favor coverage of selected geographical regions while maintaining said continuous global line-of-sight visibility.

14. The satellite constellation of claim 12 wherein the axis of symmetry of said satellite constellation is selected so as to provide a predetermined orientation with respect to the earth.