Medium earth orbit communication satellite system

• US 5,890,679 A
• Filed: 09/26/1996
• Issued: 04/06/1999
• Est. Priority Date: 09/26/1996
• Status: Expired due to Term

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: Loral Aerospace Corp. (MHR Holdings LLC (New York))
• Inventors: Chethik, Frank
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US08/718,958
• Time in Patent Office: 922 Days
• Field of Search: 244/158 R, 455/427-430, 455/12.1-13.4
• US Class Current: 244/158.4
• 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 7/195 Non-synchronous stations

Abstract

A Medium Earth Orbit (MEO) satellite constellation comprising two satellite subconstellations. Each of the two satellite subconstellations comprises three cross-linked satellites. The cross-linked satellites of both subconstellations lay within or near the equatorial plane, and follow a substantially circular orbit. Individual ones of the satellites within each respective subconstellation are offset from each of two adjacent satellites of at least one of the other subconstellations by a predetermined angle. Each of the satellite subconstellations relays communications between a terrestrial node and at least one mission platform in manner that minimizes the number of satellite links necessary for relaying the communications. At least one satellite from each respective subconstellation is always within a view of the terrestrial node.

Claims

1. A Medium Earth Orbit (MEO) satellite constellation, comprising:

a first subconstellation comprising a first group of three cross-linked satellites lying in an equatorial plane; and

a second subconstellation comprising a second group of three cross-linked satellites lying in the equatorial plane;

wherein each of the satellites of the first subconstellation is offset from each of two adjacent satellites of the second subconstellation by approximately a same predetermined angle, and wherein each of the satellites of the second subconstellation is offset from each of two adjacent satellites of the first subconstellation by approximately the same predetermined angle.

2. A satellite constellation as set forth in claim 1, wherein the predetermined angle is approximately 60°

.

3. A satellite constellation as set forth in claim 1, wherein at least one satellite from respective ones of the first and second subconstellations is always within view of each of a terrestrial node and at least one mission platform.

4. A satellite constellation as set forth in claim 3, wherein the at least one mission platform includes at least one of a satellite in low earth orbit, an aircraft, and a terrestrial-based user-communication system.

5. A satellite constellation as set forth in claim 1, wherein each of the plurality of satellites of each of the first and second subconstellations follows a substantially circular orbit.

6. A satellite constellation as set forth in claim 1, wherein each cross-linked satellite of each of the first and second subconstellations comprises:

means for receiving a signal from at least one of a terrestrial node, a mission platform, and another one of the cross-linked satellites, and for providing the received signal to an output of said receiving means; and

means, coupled to the output of said receiving means, for forwarding a signal output by said receiving means to at least one of the terrestrial node, the mission platform, and another one of the cross-linked satellites in accordance with command information received from the terrestrial node.

7. A method for providing a signal between a terrestrial node and at least one mission platform via a Medium Earth Orbit (MEO) satellite constellation, comprising the steps of:

providing the MEO satellite constellation so as to comprise at least a first and a second subconstellation, the first subconstellation comprising at least three cross-linked satellites for relaying signals received by the first subconstellation in a predetermined manner, the second subconstellation comprising at least three cross-linked satellites for relaying signals received by the second subconstellation in a predetermined manner, the cross-linked satellites of both of the first and second subconstellations lying in a same orbital plane;

selecting one of the first and second subconstellations which can relay the signal between the terrestrial node and the at least one mission platform in a manner that minimizes a number of satellite cross-links;

transmitting the signal from the terrestrial node to the selected one of the subconstellations, the signal carrying at least a downlink command; and

based upon the downlink command, downlinking at least a portion of the signal from the selected subconstellation to the at least one mission platform, wherein the orbital plane is an equatorial plane.