Method and apparatus for selectively operating satellites in tundra orbits

• US 7,136,640 B2
• Filed: 06/13/2002
• Issued: 11/14/2006
• Est. Priority Date: 11/04/1999
• Status: Expired due to Fees

• Current Assignee: Sirius XM Radio Inc. (Liberty Media Corporation)
• Original Assignee: XM Satellite Radio Incorporated (Liberty Media Corporation)
• Inventors: Marko, Paul D.
• Primary Examiner(s): Ferguson, Keith
• Application Number:
  US10/171,619
• Publication Number:
  US 20020151273A1
• Time in Patent Office: 1,615 Days
• Field of Search: 455/427, 455/428, 455/430, 455/431, 455/3.01, 455/3.02, 455/12.1, 455/13.1, 455/422.1, 455/403, 455/500, 455/517, 375/316, 375/260
• US Class Current: 455/428
• CPC Class Codes: H04B 7/18534 for enhancing link reliablility, e.g. satellites diversity
• CPC Class Codes: H04B 7/195 Non-synchronous stations

Abstract

A satellite system provides geosynchronous satellites in tundra orbits in respective elliptical orbital planes separated by 120 degrees. The satellites traverse a common figure-eight ground track comprising northern and southern loops. The satellites are controllably switched to operate the satellite currently traversing the northern loop to deliver a selected signal (e.g., a selected frequency signal) to satellite receivers.

Claims

1. A method for controlling first and second geosynchronous satellites in tundra orbits in respective orbital planes in a satellite communication system, the satellite communication system providing at least one of a first frequency signal and a second frequency signal to receivers, the satellites each traversing a common ground track having a northern loop, a southern loop, and a crossover point between the northern and southern loops, the method comprising the steps of:

selecting said first frequency satellite signal to be transmitted from whichever of said first and second geosynchronous satellites is traversing said northern loop;

monitoring when said first and second geosynchronous satellites enter said northern loop and exit said northern loop; and

switching via a satellite command system said first frequency signal to one of said first and second geosynchronous satellites when said satellite enters said northern loop.

2. A method as claimed in claim 1, further comprising the step of switching via said satellite command system said second frequency signal to said satellite when said satellite exits said northern loop.

3. A method as claimed in claim 2, further comprising the step of powering down said satellite when said satellite descends said southern loop below the equator.

4. A method as claimed in claim 3, further comprising the step of powering on said satellite when said satellite ascends said southern loop from the equator.

5. A method as claimed in claim 4, further comprising the step of switching via said satellite command system said first frequency signal to said satellite when said satellite enters said northern loop.

6. A method for controlling first and second geosynchronous satellites in tundra orbits in respective orbital planes in a satellite communication system, the satellite communication system providing at least one of a first frequency signal and a second frequency signal to receivers, the satellites each traversing a common ground track having a northern loop, a southern loop, and a crossover point between the northern and southern loops, the method comprising the steps of:

selecting said first frequency satellite signal to be transmitted from whichever of said first and second geosynchronous satellites is traversing said northern loop;

monitoring the locations of said first and second geosynchronous satellites along said ground track; and

switching via a satellite command system said first frequency signal to whichever of said first and second geosynchronous satellites is near said crossover point and one of entering said northern loop and traversing said northern loop.

7. A method as claimed in claim 6, further comprising the step of switching said second frequency signal to the other of said first and second geosynchronous satellites when said satellite is near said crossover point and one of approaching said crossover point to exit said northern loop and descending said southern loop.

8. A method for controlling first, second and third geosynchronous satellites in three inclined, elliptical orbits that are separated by approximately 120 degrees in a satellite communication system, the satellite communication system providing at least one of a first frequency signal and a second frequency signal to receivers, the satellites each traversing a common ground track having a northern loop, a southern loop, and a crossover point between the northern and southern loops, the method comprising the steps of:

powering on a first satellite that is ascending said southern loop from the equator;

operating a second satellite at apogee to transmit said first frequency signal to said receivers;

powering down a third satellite after descending said southern loop below the equator, said third satellite having operated to provide said second frequency signal to said receivers prior to reaching an orbital position near the equator;

operating said first satellite to transmit said first frequency signal when said first satellite reaches said crossover point and while said first satellite traverses said northern loop; and

switching operation of said second satellite to transmit said second frequency signal when said second satellite traverses said crossover point to commence descent of said southern loop.

9. A method as claimed in claim 8, further comprising the steps of:

powering up said third satellite after ascending said southern loop from the equator; and

switching operation of said third satellite to transmit said first frequency signal when said second satellite traverses said crossover point to commence ascent of said northern loop.

10. A method as claimed in claim 8, further comprising the step of powering down said second satellite when said second satellite traverses said southern loop below the equator.

11. A method for controlling first, second and third geosynchronous satellites in three inclined, elliptical orbits that are separated by approximately 120 degrees in a satellite communication system, the satellite communication system providing at least one of a first frequency signal and a second frequency signal to receivers, the satellites each traversing a common ground track having a northern loop, a southern loop, and a crossover point between the northern and southern loops, the method comprising the steps of:

powering on a first satellite that is ascending said southern loop from the equator;

operating a second satellite at apogee to transmit said first frequency signal to said receivers;

powering down a third satellite after descending said southern loop below the equator, said third satellite having operated to provide said second frequency signal to said receivers prior to reaching an orbital position near the equator;

switching said first satellite to said first frequency signal when said first satellite is near said crossover point; and

switching operation of said second satellite to transmit said second frequency signal when said second satellite is near said crossover point and one of approaching said crossover point to exit said northern loop and descending said southern loop.

12. A method as claimed in claim 11, further comprising the steps of:

powering up said third satellite after ascending said southern loop from the equator; and

switching operation of said third satellite to transmit said first frequency signal when said third satellite is near said crossover point and one of one of approaching said crossover point to enter said northern loop and ascending said southern loop.

13. A method as claimed in claim 11, further comprising the step of powering down said second satellite when said second satellite traverses said southern loop below the equator.

14. A satellite command system for use in a satellite communication system comprising first, second and third geosynchronous satellites in three inclined, elliptical orbits that are separated by approximately 120 degrees, the satellite traversing a common ground track having a northern loop, a southern loop, and a crossover point between the northern and southern loops, the satellite communication system comprising a first uplink device for transmitting a first frequency satellite signal and a second uplink device for transmitting a second frequency satellite signal, the satellite command system comprising:

at least one of an input device to receive data indicating the location of said satellites along said common ground path, and a device to determine and generate said data relating to the location of said satellites along said common ground path; and

a processing device for generating commands depending on said data, said processing device being programmed to generate a first command to operate said first uplink device to transmit said first frequency satellite signal to whichever one of said satellites that is traversing said northern loop, and a second command to operate said second uplink device to transmit said second frequency satellite signal to whichever one of said satellites that is traversing said southern loop.

15. A satellite command system as claimed in claim 14, wherein said processing device is programmed to generate a command to power down whichever one of said satellites is traversing said southern loop below said equator.