Elliptical orbit satellite, system, and deployment with controllable coverage characteristics

• US 5,788,187 A
• Filed: 08/22/1994
• Issued: 08/04/1998
• Est. Priority Date: 06/02/1992
• Status: Expired due to Fees

• Current Assignee: ESBH, Inc.
• Original Assignee: Mobile Communications, Inc.
• Inventors: Brosius, Jay, Castiel, David, Draim, John, Schor, Matthew
• Primary Examiner(s): MARQUIS, LISSI MOJICA
• Application Number:
  US08/292,964
• Time in Patent Office: 1,443 Days
• Field of Search: 244/158 R, 379/59, 379/60, 455/12.1, 455/13.1, 455/13.2, 455/13.3, 392/352, 392/354, 392/355, 392/356, 392/357
• US Class Current: 455/12.1
• CPC Class Codes: B64G 1/002 Launch systems
• 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: H04B 7/18576 Satellite systems for providing narrowband data service to fixed or mobile stations, e.g. using a minisatellite, a microsatellite for selecting H04W
• CPC Class Codes: H04B 7/195 Non-synchronous stations

Abstract

An elliptical orbit satellite system which describes communication and TT&C with ground stations. Earth stations are located for the circular orbiting satellite in a way such that the line of sight can never include geo synchronous satellites. The ground stations for the elliptically orbiting satellites monitor the position of the satellite, and no antenna communicates with a satellite which is in direct line of sight between the antenna and a geo satellite. Another aspect of the invention locates two TT&C stations, separated in longitude by 90° and configures these stations such that each satellite in each constellation will be able to communicate with one of the two TT&C stations once during each satellite rotation period.

Claims

1. A method of communicating between a ground station on Earth and a constellation of satellites orbiting around the Earth, comprising the steps of:

orienting a first ground antenna in said ground station to follow a first orbiting satellite so that said first orbiting satellite remains illuminated by a beam from said first ground antenna, whereby said first ground antenna communicates with said first orbiting satellite;

monitoring a position of said first ground antenna;

calculating an area where said beam from said first ground antenna will illuminate, and determining if said beam could interfere with a transmission to another satellite; and

ceasing transmission of said beam from said first ground antenna to said first orbiting satellite when determining that said beam could interfere.

2. A method as in claim 1 comprising the further steps of using a second ground antenna to communicate with a second satellite after said ceasing step by orientating said second ground antenna to follow and illuminate said second satellite.

3. A method as in claim 2 wherein said communication with said first and second satellites is on a same band as communication with geosynchronous satellites.

4. A method as in claim 3 wherein said band is C band.

5. A method as in claim 1, wherein said orbits are inclined elliptical orbits.

6. A method as in claim 1, wherein said orbits are circular or slightly elliptical.

8. A method as in claim 5 wherein said ground stations are located at greater than 5°

north latitude.

9. A method as in claim 1 wherein said first and second ground antennas are at locations between 10°

and 40°

north latitude.

7. A method of communicating with a low earth orbit satellite comprising:

locating a ground station at a location where the low earth orbit satellite will always appear in a field of view at a position which is lower than locations of equatorial geosynchronous satellites, by an amount of separation at least equal to a beam width; and

communicating with said satellites with a beam which has a width equal to or smaller than said amount of separation.

10. An inclined elliptic satellite system and tracking system, comprising:

a plurality of satellites in an inclined elliptic orbit, each of said satellites including communication equipment thereon;

at least one Earth station on the earth having at least one ground antenna operable to track said satellites orbiting around the earth, communicating with said plurality of satellites, said earth station including means for determining a position of each satellite relative to another satellite, and for commanding communication with a different satellite when said position would otherwise interfere with said another satellite;

a second plurality of satellites, in a circular or slightly elliptical orbit which is lower than geosynchronous,

wherein said at least one Earth station is located at a location where the low Earth orbit satellite will always appear in a field of view at a position which is lower than locations of equatorial geosynchronous satellites, by an amount of separation at least equal to a width of a beam used to communicate with the satellites; and

communicating with said satellites with a beam width equal to or smaller than said amount of separation.

11. A method of communicating between ground stations fixed on Earth and a constellation of satellites orbiting around the Earth, comprising:

deploying a plurality of satellites orbiting around the earth in a predetermined constellation;

distributing a plurality of ground stations for tracking, telemetry and control at selected station locations relative to one another in the northern hemisphere of the Earth, each of said ground stations having at least one ground antenna that can be orientated to track satellites by illuminating a radio beam thereon, said station locations and said constellation being so determined that each and every of said satellites is always in view of at least one of said ground stations;

determining whether a first radio beam emitted from a first ground antenna of said ground stations that illuminates a first satellite in said constellation could interfere with a transmission to another satellite; and

ceasing said first radio beam to said first satellite when said first radio beam is determined to interfere.

12. A method as in claim 11, wherein:

said constellation forms a medium earth orbit array with an orbital altitude greater than about 4000 km; and

said ground stations include at least a first ground station and a second ground station in a mid-latitude range of the northern hemisphere that are separated with respect to each other in longitude by about 90 degrees.

13. A method as in claim 12, further comprising using a second ground antenna to communicate with a second satellite after said ceasing step by orientating said second ground antenna to follow and illuminate said second satellite.

14. An inclined elliptic satellite system and tracking system, comprising:

a plurality of satellites in an inclined elliptic orbit, each of said satellites including communication equipment thereon;

at least one earth station on the earth having at least one ground antenna operable to track said satellites orbiting around the earth, communicating with said plurality of satellites, said earth station including means for determining a position of each satellite relative to another satellite, and for commanding communication with a different satellite when said position would otherwise interfere with said another satellite.