Satellite constellations using nodally-adjusted repeating ground track orbits
A satellite system and method is disclosed. A plurality of satellites includes one or more satellites in circular orbits and at least one satellite of the plurality of satellites in an elliptcal orbit. Each of the plurality of satellites has substantially the same nodal regression rate. An exemplary constellation uses an inclination of substantially 63.43°. The elliptical orbit can be implemented by a refuelable satellite used to make low perigee passes over a location of interest.
1. A satellite system comprising:
a satellite constellation including a plurality of satellites orbiting a planet to provide a coverage pattern of the planet the plurality of satellites including:
one or more satellites in circular orbits; and
at least one satellite of the plurality of satellites in an elliptical orbit having a perigee less than an altitude of the circular orbits and an apogee greater than the altitude of the circular orbits;
wherein each of the circular orbits and the at least one elliptical orbit are disposed at the same inclination, and each of the plurality of satellites has substantially the same nodal regression rate.
2. The system of claim 1 , wherein the elliptical orbit of the at least one satellite includes at least one low perigee pass over a location of interest.
3. The system of claim 1 , wherein the plurality of satellites each have an inclination of substantially 63.43°.
4. The system of claim 1 , wherein the circular orbits each have an altitude of substantially 1500 km and the elliptical orbit has an elliptical altitude of substantially 237 km×3046 km.
5. The system of claim 1 , wherein the satellite constellation provides the coverage pattern for the plurality of satellites to perform observation of the planet.
6. The system of claim 1 , wherein the sattelite constellation provides the coverage pattern for the plurality of satellites to provide communication for the planet.
7. The system of claim 1 , wherein the plurality of satellites includes a plurality of elliptically orbiting satellites.
8. The system of claim 7 , wherein the plurality of elliptically orbiting satellites comprises a row of satellites each having a different right ascension of ascending node and initial mean anomaly.
9. The system of claim 7 , wherein the plurality of elliptically orbiting satellite comprises a group of satellites in a plane of a common right ascension of ascending node.
10. The system of claim 9 , wherein the plurality of elliptically orbiting satellites further comprises a second group of satellites in a second plane of a second common right ascension of ascending node.
11. The system of claim 1 , wherein at least one satellite in the elliptical orbit is a refuelable satellite having fuel replinished at least once to allow the refuelable satellite to be redeployed from one of the circular orbits into the elliptical orbit.
12. The system of claim 11 , wherein the elliptical orbit of the refuelable satellite includes a low perigee pass over a location of interest.
13. The system of claim 1 , wherein the .plurality of satellites produce repeating ground tracks.
14. The system of claim 13 , wherein the repeating ground tracks repeat more than once daily.
15. The system of claim 13 , wherein the repeating ground tracks repeat approximately one time per day.
16. A method comprising the steps of:
maintaining a satellite constellation including a plurality of satellites orbiting a planet to provide a coverage pattern of the planet, including:
providing one or more satellites in circular orbits; and
providing at least one satellite of the plurality of satellites in an elliptical orbit having a perigee less than an altitude of the circular orbits and an apogee greater than the altitude of the circular orbits;
where each of the circular orbits and the at least one elliptical orbit are disposed at the same inclination, and each of the plurality of satellites has substantially the same nodal regression rate.
17. The method of claim 16 , wherein the elliptical orbit of the at least one satellite includes at least one low perigee pass over a location of interest.
18. The method of claim 16 , wherein the plurality of satellites each have an inclination of substantially 63.43°.
19. The method of claim 16 , wherein the circular orbits each have an altitude of substantially 1500 km and the elliptical orbit has an elliptical altitude of substantially 237 km×3046 km.
20. The method of claim 16 , wherein the satellite constellation provides the coverage pattern for the plurality of satellites to perform observation of the planet.
21. The method of claim 16 , wherein the satellite constellation provides the coverage pattern for the plurality of satellites to provide communication for the planet.
22. The method of claim 16 , wherein the plurality of satellites includes a plurality of elliptically orbiting satellites.
23. The method of claim 22 , wherein the plurality of elliptically orbiting satellites comprises a row of satellites each having a different right ascension of ascending node and initial mean anomaly.
24. The method of claim 22 , wherein the plurality of elliptically orbiting satellites comprises a group of satellites in a plane of a common right ascension of ascending node.
25. The method of claim 24 , wherein the plurality of elliptically orbiting satellites further comprises a second group of satellites in a second plane of a second common right ascension of ascending node.
26. The method of claim 16 , wherein at least one satellite in the elliptical orbit is a refuelable satellite having fuel replenished at least once to allow the refuelable satellite to be redeployed from one of the circular orbits into the elliptical orbit.
27. The method of claim 26 , wherein the elliptical orbit of the refuelable satellite includes a low perigee pass over a location of interest.
28. The method of claim 16 , wherein the plurality of satellites produce repeating ground tracks.
29. The method of claim 28 , wherein the repeating ground tracks repeat more than once daily.
30. The method of claim 28 , wherein the repeating ground tracks repeat approximately one time per day.
31. A method comprising the steps of:
maintaining a satellite constellation including a plurality of satellites orbiting a planet to provide a coverage pattern of the planet, including:
deploying one or more satellites in a plurality of circular orbits, each having a nodal regression;
redeploying at least one satellite in at least one of the plurality of circular orbits into an elliptical orbit;
adjusting an eccentricity of the elliptical orbit to provide the elliptical orbit the nodal regression,
wherein each of the circular orbits and the at least one elliptical orbit are disposed at the same inclination, and each of the plurality of satellites has substantially the same nodal regression rate.
32. The method of claim 31 , wherein the elliptical orbit of the at least one satellite includes at least one low perigee pass over a location of interest.
33. The method of claim 31 , wherein the plurality of satellites each have an inclination of substantially 63.43°.
34. The method of claim 31 , wherein the circular orbits each have an altitude of substantially 1500 km and the elliptical orbit has an elliptical altitude of substantially 237 km×3046 km.
35. The method of claim 31 , wherein at least one satellite in the elliptical orbit is a refuelable satellite having fuel replenished at least once to allow the refuelable satellite to use the elliptical orbit.
36. The method of claim 35 , wherein the elliptical orbit of the refuelable satellite includes a low perigee pass over a location of interest.