Satellite system and method for global coverage
A non-geostationary satellite system and method for weather and climate monitoring, communications applications, scientific research, and similar tasks. The satellite system provides global coverage using a constellation of six satellites in two orthogonal, 24 sidereal hour orbits (geosynchronous) with inclinations of 70° to 90°, and eccentricities of 0.275-0.45. By placing three of the satellites in a first orbit with an apogee over the north pole, and three of the satellites in a second, orthogonal orbit with an apogee over the south pole, global coverage may be obtained. As well, the satellites in these orbits avoid most of the Van Allen Belts.
1. A satellite system for global coverage comprising:
a constellation of six satellites, three of said satellites orbiting in a first orbit and the other three of said satellites orbiting in a second orbit;
at least one base station being configured to transmit to, and receive signals from said constellation of six satellites;
a flight control system for controlling said constellation of six satellites such that:
the first orbit has an orbital inclination between 70° and 90°, an apogee over the northern hemisphere, a perigee that avoids an inner Van Allen belt of high energy protons, and an orbital eccentricity of greater than 0.28 and less than 0.45;
the second orbit has an orbital inclination between 70° and 90°, an apogee over the southern hemisphere, a perigee that avoids the inner Van Allen belt of high energy protons, and an orbital eccentricity of greater than 0.28 and less than 0.45; and
a major axis of the first orbit is substantially aligned with a major axis of the second orbit, and planes of the first orbit and the second orbit being orthogonal to one another.
2. The system of claim 1 wherein the orbital eccentricity and the orbital inclination of each of the first and second orbits are selected to provide 99% global coverage, with an elevation angle of at least 10°.
3. The system of claim 1 , wherein the orbital inclination of each of the first and second orbits is between 80° and 90°.
4. The system of claim 1 , wherein the orbital inclination of each of the first and second orbits is 90°.
5. The system of claim 1 , wherein the orbital eccentricity and the orbital inclination of each of the first and second orbits are selected to provide continuous global coverage, with an elevation angle of at least 8.7°.
6. The system of claim 1 , wherein the orbital eccentricity of each of the first and second orbits is between 0.30 and 0.34.
7. The system of claim 1 , wherein the satellites have an orbital period of one sidereal day.
8. The system of claim 1 , wherein phasing of the satellites is such that a time between their respective apogees is an orbital period divided by a number of satellites in the constellation.
9. The system of claim 1 , wherein changes in satellite orbital perturbations are compensated for by on-board propulsion systems.
10. The system of claim 1 , wherein directional antennas are used for communications between the satellites and the base station.
11. The system of claim 1 , wherein the base station is operable to track the satellites across the sky.
12. The system of claim 1 , wherein the base station is operable to hand off communications between the satellites as they move across the sky.
13. The system of claim 1 , wherein the satellites include a meteorological monitoring payload.
14. The system claim 1 , wherein the satellites include a communications payload.
15. The system of claim 1 , wherein the satellites include a scientific research payload.
16. The system of claim 1 , wherein the orbital eccentricity and the orbital inclination of each of the first and second orbits are selected to result in a 50 krad radiation exposure over 15 years, allowing the use of conventional GEO satellite shielding.
17. A method of operation for a satellite system for Earth observation and communications having global coverage, comprising:
providing a constellation of six satellites, three of said satellites orbiting in a first orbit and the other three of said satellites orbiting in a second orbit;
the first orbit having an orbital inclination between 70° and 90°, an apogee over the northern hemisphere, a perigee that avoids an inner Van Allen belt of high energy protons, and an orbital eccentricity of greater than 0.28 and less than 0.45;
the second orbit having an orbital inclination between 70° and 90°, an apogee over the southern hemisphere, a perigee that avoids the inner Van Allen belt of high energy protons, and an orbital eccentricity of greater than 0.28 and less than 0.45; and
a major axis of the first orbit being substantially aligned with a major axis of the second orbit, and planes of the first orbit and the second orbit being orthogonal to one another; and
providing at least one base station for transmitting to and receiving signals from said constellation of six satellites.
18. The method of claim 17 , wherein the orbital inclination of each of the first and second orbits is between 80° and 90°.
19. The method of claim 17 , wherein the orbital eccentricity of each of the first and second orbits is between 0.30 and 0.34.
20. The method of claim 17 , wherein the satellites have an orbital period of one sidereal day.
21. The method of claim 17 , wherein phasing of the satellites is such that a time between their respective apogees is an orbital period divided by a number of satellites in the constellation.
22. A satellite base station, comprising:
a communication system for transmitting and receiving signals to and from a constellation of six satellites providing global coverage; and
a flight control system for controlling said constellation of six satellites such that:
three of said satellites orbit in a first orbit and the other three of said satellites orbit in a second orbit;
the first orbit having an orbital inclination between 70° and 90° with respect to a first pole of the Earth, an orbital eccentricity of greater than 0.28 and less than 0.45, and a perigee that avoids an inner Van Allen belt of high energy protons;
the second orbit having an orbital inclination between 70° and 90° with respect to a second pole of the Earth, an orbital eccentricity of greater than 0.28 and less than 0.45, and a perigee that avoids the inner Van Allen belt of high energy protons; and
a major axis of the first orbit being substantially aligned with a major axis of the second orbit, and planes of the first orbit and the second orbit being orthogonal to one another.
23. The satellite base station of claim 22 , wherein the orbital inclination of each of the first and second orbits is between 80° and 90°.
24. The satellite base station of claim 22 , wherein the orbital eccentricity of each of the first and second orbits is between 0.30 and 0.34.
25. The satellite base station of claim 22 , wherein the satellites have an orbital period of one sidereal day.
26. The satellite base station of claim 22 , wherein phasing of the satellites is such that a time between their respective apogees is an orbital period divided by a number of satellites in the constellation.