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US 9,309,010 B2Granted
Methods and apparatus for controlling a plurality of satellites using node-synchronous eccentricity control
AssigneeThe Boeing Company
InventorYiu-hung M. Ho
Life of this patent
Estimating the term…
Abstract
A first inclination vector associated with a first satellite of the plurality of satellites is established. A second inclination vector associated with a second satellite of the plurality of satellites is established. The first satellite and the second satellite are controlled, such that the first satellite and the second satellite are synchronized with a node.
Claims20
A method for controlling a plurality of satellites, the method comprising:
- establishing a first inclination vector associated with a first satellite of the plurality of satellites, the first satellite travelling in a first inclined geosynchronous orbit;
- establishing a second inclination vector associated with a second satellite of the plurality of satellites, the second satellite travelling in a second inclined geosynchronous orbit;
- and
- controlling the first satellite and the second satellite such that the first satellite and the second satellite are synchronized with a node, wherein the first and second inclination vectors are offset from each other such that a radial offset is defined between orbital paths of the first and second satellites at the node, and such that latitude separation is defined between the orbital paths of the first and second satellites away from the node.
1 more element
A control system for controlling a plurality of satellites, said control system comprising:
- a memory device containing a first inclination vector associated with a first satellite of the plurality of satellites, and a second inclination vector associated with a second satellite of the plurality of satellites, the first satellite travelling in a first inclined geosynchronous orbit, and the second satellite travelling in a second inclined geosynchronous orbit;
- and
- a processing device configured to control the first satellite and the second satellite such that the first satellite and the second satellite are synchronized with a node, wherein the first and second inclination vectors are offset from each other such that a radial offset is defined between orbital paths of the first and second satellites at the node, and such that latitude separation is defined between the orbital paths of the first and second satellites away from the node.
Dependencies are inferred from the claim text.