INCLINED ORBIT SATELLITE SYSTEMS

• US 20150158602A1
• Filed: 05/21/2014
• Published: 06/11/2015
• Est. Priority Date: 12/11/2013
• Status: Abandoned Application

• Current Assignee: Tawsat Limited
• Original Assignee: Tawsat Limited
• Inventors: MARSHACK, David, FREEDMAN, Jeffrey
• Application Number:
  US14/284,113
• Publication Number:
  US 20150158602A1
• Time in Patent Office: Days
• US Class Current: 1/1
• 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: B64G 1/2425 Geosynchronous orbits
• CPC Class Codes: B64G 1/66 Arrangements or adaptations of apparatus or instruments, not otherwise provided for
• CPC Class Codes: H01Q 1/288 Satellite antennas
• CPC Class Codes: H01Q 3/20 wherein the primary active element is fixed and the reflecting device is movable
• CPC Class Codes: H01Q 3/24 varying the orientation by switching energy from one active radiating element to another, e.g. for beam switching
• CPC Class Codes: H04B 7/185 Space-based or airborne stations; Stations for satellite systemsH04B7/204 takes precedence
• CPC Class Codes: H04B 7/19 Earth-synchronous stations

Abstract

The present disclosure is directed to an inclined geosynchronous orbit satellite system that can efficiently provide continuous communication to multiple geographic regions across the world using satellites in inclined geosynchronous orbital paths having an equatorial crossing and enabling the reuse of frequencies assigned within GSO orbital locations. The inclined orbit satellite system can include multiple inclined orbit satellites that are capable of co-existing with geostationary satellites to provide continuous uninterrupted service.

Claims

1. A method comprising:

providing a first satellite that travels an inclined geosynchronous orbital path having an equatorial crossing,

preventing transmissions between the first satellite and Earth stations when the first satellite travels at least a first portion of the path,

permitting transmissions between the first satellite and Earth stations when the first satellite travels at least a second portion of the path, the first portion of the path being relatively closer to the equatorial crossing than the second portion of the path.

2. The method of claim 1 comprising:

providing a second satellite that travels the inclined geosynchronous orbital path,

preventing transmissions between the second satellite and Earth stations when the second satellite travels at least the first portion of the path, and

permitting transmissions between the second satellite and Earth stations when the second satellite travels at least the second portion of the path.

3. The method of claim 2 comprising:

establishing relative spacing between the first and second satellites which enables transmissions between at least one of the first and second satellites and Earth stations at any time.

4. The method of claim 2 comprising:

providing a third satellite that travels the inclined geosynchronous orbital path,

preventing transmissions between the third satellite and Earth stations when the third satellite travels at least the first portion of the path, and

permitting transmissions between the third satellite and Earth stations when the third satellite travels at least the second portion of the path.

5. The method of claim 4 comprising:

establishing relative spacing among the first, second and third satellites which enables transmissions between at least two of the first, second and third satellites and Earth stations at any time.

6. The method of claim 4, wherein at least one of the first, second, and third satellites is configured to be a backup satellite for any other satellite in the same orbital plane as the first, second, and third satellites.

7. A system comprising:

a first satellite that travels an inclined geosynchronous orbital path having an equatorial crossing,

a transmitter in the first satellite that attenuates transmissions between the first satellite and Earth stations when the first satellite travels at least a first portion of the path, wherein the attenuated transmissions prevent interference with transmissions between geostationary satellites and Earth stations,

a transmitter in the first satellite that permits unattenuated transmissions between the first satellite and Earth stations when the first satellite travels at least a second portion of the path, the first portion of the path being relatively closer to the equatorial crossing than the second portion of the path.

8. The system of claim 7 comprising:

a second satellite that travels the inclined geosynchronous orbital path,

a transmitter in the second satellite that attenuates transmissions between the second satellite and Earth stations when the second satellite travels at least the first portion of the path,

a transmitter in the second satellite that permits unattenuated transmissions between the second satellite and Earth stations when the second satellite travels at least the second portion of the path.

9. The system of claim 8, wherein the first and second satellites are relatively spaced to enable transmissions between at least one of the first and second satellites and Earth stations at any time.

10. The system of claim 8 comprising:

a third satellite that travels the inclined geosynchronous orbital path,

a transmitter in the third satellite that attenuates transmissions between the third satellite and Earth stations when the third satellite travels at least the first portion of the path, and

a transmitter in the third satellite that permits unattenuated transmissions between the third satellite and Earth stations when the third satellite travels at least the second portion of the path.

11. The system of claim 10, wherein the first, second and third satellites are relatively spaced to enable transmissions between at least two of the first, second and third satellites and Earth stations at any time.

12. The system of claim 10, wherein at least one of the first, second, and third satellites is configured to be a backup satellite for any other satellite in the same orbital plane as the first, second, and third satellites.

13. A system comprising:

a first satellite that travels an inclined geosynchronous orbital path having an equatorial crossing,

a transmitter in an Earth station that attenuates transmissions between the Earth station and the first satellite when the first satellite travels at least a first portion of the path, the attenuated transmissions prevent interference with transmissions between geostationary satellites and Earth stations,

a transmitter in the Earth station that permits unattenuated transmissions between the Earth station and the first satellite when the first satellite travels at least a second portion of the path, the first portion of the path being relatively closer to the equatorial crossing than the second portion of the path.

14. The system of claim 13 comprising:

a second satellite that travels the inclined geosynchronous orbital path,

a transmitter in the Earth station that attenuates transmissions between the Earth station and the second satellite when the second satellite travels at least a first portion of the path,

a transmitter in the Earth station that permits unattenuated transmissions between the Earth station and the second satellite when the second satellite travels at least a second portion of the path.

15. The system of claim 14, wherein the first and second satellites are relatively spaced to enable transmissions between at least one of the first and second satellites and Earth stations at any time.

16. The system of claim 14 comprising:

a third satellite that travels the inclined geosynchronous orbital path,

a transmitter in the Earth station that attenuates transmissions between the Earth station and the third satellite when the third satellite travels at least a first portion of the path,

a transmitter in the Earth station that permits unattenuated transmissions between the Earth station and the third satellite when the third satellite travels at least a second portion of the path.

17. The system of claim 16, wherein the first, second, and third satellites are relatively spaced to enable transmissions between at least two of the first, second and third satellites and Earth stations at any time.

18. The system of claim 16, wherein at least one of the first, second, and third satellites is configured to be a backup satellite for any other satellite in the same orbital plane as the first, second, and third satellites.

19. A method comprising:

receiving a transmission originating from a first satellite when the first satellite travels at least a first portion of an inclined geosynchronous orbital path having an equatorial crossing,

not receiving a transmission originating from the first satellite when the first satellite travels at least a second portion of an inclined geosynchronous orbital path having an equatorial crossing, the first portion of the path being relatively closer to the equatorial crossing than the second portion of the path.

20. The method of claim 19 comprising:

receiving a transmission originating from a second satellite when the second satellite travels at least the first portion of the inclined geosynchronous orbital path having an equatorial crossing,

not receiving a transmission originating from the second satellite when the second satellite travels at least the second portion of the inclined geosynchronous orbital path having an equatorial crossing.

21. The method of claim 20, wherein the first and second satellites are relatively spaced to enable receipt of a transmission from at least one of the first and second satellites at any time.

22. The method of claim 20 comprising:

receiving a transmission originating from a third satellite when the third satellite travels at least the first portion of the inclined geosynchronous orbital path having an equatorial crossing,

not receiving a transmission originating from the third satellite when the third satellite travels at least the second portion of the inclined geosynchronous orbital path having an equatorial crossing.

23. The method of claim 22 wherein the first, second and third satellites are relatively spaced to enable receipt of a transmission from at least two of the first, second and third satellites at any time.

24. The method of claim 22, wherein at least one of the first, second, and third satellites is configured to be a backup satellite for any other satellite in the same orbital plane as the first, second, and third satellites.

25. An antenna system comprising:

a reflector configured to reflect signals to and from a satellite traveling an inclined geosynchronous orbital path having an equatorial crossing,

at least one feed element array configured to receive signals from the reflector and transmit signals to the reflector,

a transmit unit connected to the at least one feed element array configured to transmit signals for communication with the satellite to the at least one feed array,

a receiver unit connected to the at least one feed element array configured to receive and process signals from the at least one feed element array,

wherein the antenna system is configured to communicate with the satellite when the satellite travels at least a first portion of the path being relatively farther from the equatorial crossing than a second portion of the path.

26. The system of claim 25, further comprising a control unit configured to control the reflector, the at least one feed element array, the receiver unit, and the transmit unit in order to track the satellite throughout its inclined geosynchronous orbital path.

27. The system of claim 25, wherein the at least one feed element array comprises an upper latitude feed element array and a lower latitude feed element array.

28. The system of claim 25, wherein the antenna system is configured to continuously communicate with at least one of multiple satellites traveling the inclined geosynchronous orbital path.

29. The system of claim 25, wherein the antenna system is configured to continuously communicate with at least two of multiple satellites traveling the inclined geosynchronous orbital path.