ANTENNA SYSTEM FOR MULTIPLE ORBITS AND MULTIPLE AREAS

• US 20030090412A1
• Filed: 11/09/2001
• Published: 05/15/2003
• Est. Priority Date: 11/09/2001
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Hsu, Chih-Chien, Rink, Robert, Bauer, Jack, Rao, Sudhakar
• Granted Patent: US 6,570,528 B1
• Time in Patent Office: Days
• US Class Current: 342/354
• CPC Class Codes: H01Q 1/288 Satellite antennas
• CPC Class Codes: H01Q 15/147 provided with means for controlling or monitoring the shape of the reflecting surface for scanning H01Q3/01; aerials or aerial systems providing multiple beamwidths H01Q25/002
• CPC Class Codes: H01Q 25/00 Antennas or antenna systems providing at least two radiating patterns arrangements for changing or varying the orientation or the shape of the directional pattern H01Q3/00
• CPC Class Codes: Y10S 343/02 Satellite-mounted antenna

Abstract

A synthesized reflector surface (12) for directing communication signals (27) in a communication system (10) that operates in a plurality of orbital slots and to a plurality of regions (28) within a first coverage area (30) is provided. The synthesized reflector surface (12) includes a plurality of contiguous profile surfaces (40) that form the reflector surface (12). Each of the plurality of contiguous profile surfaces (40) alters the phase of the communication signals (27) to provide a first gain for a first satellite orbit location (32) and a second gain for a second satellite orbit location (34). The plurality of contiguous profile surfaces (40) directs the signals from the location (32) in a first orientation to the first coverage area (30) or from the location (34) in a second orientation to the first coverage area (30). A method is provided for synthesizing the reflector surface (12). A satellite system (10) and a method of configuring the satellite system (10) are also provided utilizing the synthesized reflector surface (12).

Claims

1. A synthesized reflector surface for directing communication signals in a communication system that operates in a plurality of orbital slots and to a plurality of regions within a first coverage area comprising:

a plurality of contiguous profile surfaces forming the reflector surface, each of said plurality of contiguous profile surfaces altering the phase of the communication signals to provide a first gain for a first satellite orbit location and a second gain for a second satellite orbit location;

wherein said plurality of contiguous profile surfaces directs said signals from the first satellite orbit location in a first orientation to the first coverage area or from said second satellite orbit location in a second orientation to the first coverage area.

2. A reflector surface as in claim 1 wherein said plurality of contiguous profile surfaces directs said signals from a first orbital slot in a first orientation or from a second orbital slot in a second orientation to a first coverage area.

3. A reflector surface as in claim 1 wherein the plurality of contiguous profile surfaces in an orientation of a plurality of orientations transmits communication signals from a plurality of orbital slots to said first coverage area.

4. A reflector surface as in claim 1 wherein the plurality of contiguous profile surfaces transmits signals, using said plurality of profile surfaces, from within an orbital slot to multiple regions of coverage.

5. A reflector as in claim 1 wherein the gain of said plurality of contiguous profile surfaces varies according to rain-fade requirements that are associated with a plurality of regions of coverage.

6. A reflector as in claim 1 wherein the gain of said plurality of contiguous profile surfaces varies according to slant range of the synthesized reflector in a plurality of orbital slots for said first coverage area.

7. A reflector as in claim 1 wherein a first profile surface provides a first gain for a first coverage area and a second profile surface provides a second gain for said first coverage area.

8. A reflector as in claim 1 wherein said plurality of contiguous profile surfaces provide a first plurality of gains for a first coverage area and a second plurality of gains for a second coverage area.

9. A satellite system comprising:

an antenna comprising;

a synthesized reflector surface comprising;

a plurality of contiguous profile surfaces, each of said profile surfaces altering the phase of transmitted communication signals as to provide a gain for an orbital slot;

a spacecraft-steering mechanism coupled to the satellite system;

a gimball mechanism coupled to said antenna; and

a controller electrically coupled to said spacecraft-steering mechanism and said gimball mechanism, said controller adjusting pitch and roll positioning angles of the satellite system and adjusting positioning of said antenna as to transmit signals, using a profile surface from said plurality of contiguous profile surfaces, from a first location in a first orbital slot or from a second orbital slot in a second orientation to a first coverage area.

10. A reflector as in claim 9 wherein the gain of said plurality of contiguous profile surfaces varies according to rain-fade requirements that are associated with a plurality of regions of coverage.

11. A reflector as in claim 9 wherein the gain of said plurality of contiguous profile surfaces varies according to slant range of the synthesized reflector in a plurality of orbital slots for said first coverage area.

12. A method of synthesizing a reflector surface comprising:

determining a plurality of orbital slots;

determining plurality of coverage area(s) for said plurality of orbital slots;

shaping the reflector surface in response to said plurality of orbital slots and said plurality of coverage area(s) such that the reflector surface transmits communication signals to a first coverage area from one or more of said plurality of orbital slots;

computing directivity values of communication signals for said plurality of orbital slots and said plurality of coverage area(s);

determining link availability for said plurality of orbital slots and said plurality of coverage area(s) in response to said computed directivity values; and

determining whether said directivity values and said link availability have been satisfied in said shaped reflector surface.

13. A method as in claim 12 wherein shaping the reflector surface comprises iteratively modifying the reflector surface until all desired link availability requirements are achieved.

14. A method as in claim 12 wherein shaping the reflector surface comprises using a software program to determine the size, shape, material, and profile surface arrangement of the reflector.

15. A method of configuring a satellite system having an antenna with a single synthesized reflector, the method comprising:

determining a first configuration for a primary mission having a first reflector surface;

determining a second configuration for a secondary mission having a second reflector surface; and

determining a third configuration and a fourth configuration, both of which having a third reflector surface, in response to said first configuration and said second configuration to provide directivity values and link availability for both said primary mission and said secondary mission respectively.

16. A method as in claim 15 wherein determining a first configuration comprises:

determining a primary satellite location and position such that said satellite system is in communication with a sub-satellite point;

calculating a first set of directivity values for a first orbital slot and a first coverage area;

determining first link availability for said primary mission; and

determining a first reflector surface, a steering position, and pitch and roll positioning angles in response to said first directivity values and said first link availability.

17. A method as in claim 16 wherein determining a second configuration comprises:

determining a secondary satellite location and position such that said satellite system is in communication with said sub-satellite point;

calculating second directivity values for a second orbital slot and a first coverage area;

determining second link availability for said secondary mission; and

determining a second reflector surface, a steering position, and pitch and roll positioning angles in response to said second directivity values and said second link availability.

18. A method as in claim 17 wherein determining a third configuration and a fourth configuration comprises:

comparing said first configuration with said second configuration to establish configuration difference values; and

determining the synthesized reflector shape, the pitch and roll positioning angles, and the steering positions to provide directivity values and link availability for said primary mission and said secondary mission.

19. A method as in claim 18 wherein determining a third configuration and a fourth configuration further comprises adjusting said first configuration and said second configuration as to provide directivity values and link availability for said primary mission and said secondary mission.

20. A method as in claim 15 wherein said secondary mission comprises a plurality of orbital slots.