System and method for continuous broadcast service from non-geostationary orbits
A method, apparatus for providing at least near continuous broadcast services to one or more terrestrial receiver stations is disclosed. The system comprises a plurality of satellites, each satellite in an inclined, elliptical geosynchronous orbit, each satellite providing a portion of the at least near continuous broadcast service to the terrestrial receiver. In one embodiment, the system also comprises a receiver station having an legacy antenna modified so as to include a sensitivity pattern substantially matched to the track of the apparent position of the satellites actively broadcasting information to the receiver stations. The present invention is also embodied in a method for receiving at least near continuous broadcast service from at least one of a plurality of satellites at a time, each satellite in an inclined, elliptical, geosynchronous orbit.
1. A receiver station for receiving at least near continuous broadcast service from a plurality of satellites in an inclined, elliptical, geosynchronous orbit, comprising:
an antenna having a sensitivity characteristic substantially corresponding to the track of the apparent position of each of the satellites;
wherein the receiver antenna comprises a reflector having a focal line and a focal point on the focal line and a first head disposed offset from the focal point for receiving the broadcast service from the plurality of satellites in the inclined, elliptical, geosynchronous orbit and a second head disposed substantially at the focal point for receiving signals from a geostationary satellite.
2. The receiver station of claim 1 , wherein the reflector is approximately 18 centimeters in diameter, and the head is disposed approximately 7 inches offset from the focal point and approximately 4 inches offset from the focal line.
3. The receiver station of claim 1 , wherein the plurality of satellites comprises a first satellite actively servicing the terrestrial receiver, and a second satellite, wherein the apparent position of the second satellite relative to the terrestrial receiver is substantially proximate the apparent position of the first satellite relative to the terrestrial receiver when the first satellite completes providing its portion of the broadcast service.
4. A method of receiving at least near continuous broadcast service at a terrestrial receiver, comprising the steps of:
receiving a signal having a portion of the continuous broadcast service from at least one of a plurality of augmenting satellites at a time, each augmenting satellite of the plurality of satellites being in an inclined, elliptical, geosynchronous orbit; and
receiving broadcast service from at least one legacy satellite in a geostationary orbit;
wherein the plurality of augmenting satellites comprises a first augmenting satellite and a second augmenting satellite and wherein the step of providing a signal having a portion of the continuous broadcast service from at least one of the plurality of augmenting satellites at a time comprises the steps of:
receiving a signal from the first augmenting satellite actively servicing the terrestrial receiver; and
receiving a signal from the second augmenting satellite when the apparent position of the second satellite relative to the terrestrial receiver is proximate the apparent position of the first augmenting satellite relative to the terrestrial receiver.
5. The method of claim 4 , wherein the plurality of augmenting satellites comprises a first augmenting satellite actively servicing the terrestrial receiver, and a second augmenting satellite, wherein an apparent position of the second augmenting satellite relative to the terrestrial receiver is proximate the apparent position of the first augmenting satellite relative to the terrestrial receiver when the first augmenting satellite completes providing its portion of the broadcast service.
6. The method of claim 4 , wherein a track of the apparent position of the each of the augmenting satellites relative to the terrestrial receivers when the augmenting satellite is providing its portion of the at least near continuous broadcast service is closed loop.
7. The system of claim 6 , wherein the terrestrial receiver comprises an antenna having a first sensitivity characteristic corresponding to the track of the apparent position of each of the augmenting satellites and a second sensitivity characteristic corresponding to the at least one legacy satellite.
8. The system of claim 6 , wherein the track of the apparent position of each of the augmenting satellites corresponds to a sensitivity pattern of an antenna at the terrestrial receiver.
9. The method of claim 4 , wherein a track of the apparent position of the each of the augmenting satellites relative to the terrestrial receivers when the augmenting satellite is providing its portion of the at least near continuous broadcast service is teardrop-shaped.
10. The method of claim 4 , wherein the orbits of the augmenting satellites are characterized by an orbital inclination equal to 50 degrees and an eccentricity equal to 0.13.
11. The method of claim 10 , wherein the orbits of the augmenting satellites are further characterized by a period equal to 86164 seconds, an altitude at perigee equal to 30305 kilometers, and an altitude at apogee equal to 41268 kilometers.
12. A method of receiving at least near continuous broadcast service at a terrestrial receiver, comprising the steps of:
receiving a signal having a portion of the continuous broadcast service from at least one of a plurality of augmenting satellites at a time, each augmenting satellite of the plurality of satellites being in an inclined, elliptical, geosynchronous orbit; and
receiving broadcast service from at least one legacy satellite in a geostationary orbit;
wherein a track of the apparent position of the each of the augmenting satellites relative to the terrestrial receivers when the augmenting satellite is providing its portion of the at least near continuous broadcast service is closed loop, and the terrestrial receiver comprises an antenna having a first sensitivity characteristic corresponding to the track of the apparent position of each of the augmenting satellites and a second sensitivity characteristic corresponding to the at least one legacy satellite.
13. The method of claim 12 wherein the plurality of augmenting satellites comprises a first augmenting satellite and a second augmenting satellite and wherein the step of providing a signal having a portion of the continuous broadcast service from at least one of the plurality of augmenting satellites at a time comprises the steps of:
receiving a signal from the first augmenting satellite actively servicing the terrestrial receiver; and
receiving a signal from the second augmenting satellite when the apparent position of the second satellite relative to the terrestrial receiver is proximate the apparent position of the first augmenting satellite relative to the terrestrial receiver.
14. The method of claim 12 , wherein the plurality of augmenting satellites comprises a first augmenting satellite actively servicing the terrestrial receiver, and a second augmenting satellite, wherein an apparent position of the second augmenting satellite relative to the terrestrial receiver is proximate the apparent position of the first augmenting satellite relative to the terrestrial receiver when the first augmenting satellite completes providing its portion of the broadcast service.
15. The system of claim 12 , wherein the track of the apparent position of each of the augmenting satellites corresponds to a sensitivity pattern of an antenna at the terrestrial receiver.
16. The method of claim 12 , wherein a track of the apparent position of the each of the augmenting satellites relative to the terrestrial receivers when the augmenting satellite is providing its portion of the at least near continuous broadcast service is teardrop-shaped.
17. The method of claim 12 , wherein the orbits of the augmenting satellites are characterized by an orbital inclination equal to 50 degrees and an eccentricity equal to 0.13.
18. The method of claim 17 , wherein the orbits of the augmenting satellites are further characterized by a period equal to 86164 seconds, an altitude at perigee equal to 30305 kilometers, and an altitude at apogee equal to 41268 kilometers.