Elliptical orbit satellite, system, and deployment with controllable coverage characteristics
AssigneeMobile Communications Holdings, Inc.
InventorsDavid Castiel, John E. Draim, Jay Brosius
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Abstract
A special set of elliptical satellite orbits are described which allow preferential coverage of one parameter over another. According to a first modification, the orbits are retrograde, and preferentially cover one geographical location or time of day as compared with another. A second modification uses prograde orbits and allows the apogee of the orbit to be offset a constant amount with respect to the sun, to thereby cover a different time of day relative to the others. According to a special preferred mode of the invention, the apogee is always pointing towards the sun.
Claims49
A satellite in orbit around the earth, defining an elliptical orbit which has orbital parameters to satisfy the equation ##EQU10## where .OMEGA. is the right ascension of the ascending node, and .omega. is the argument of perigee, and wherein said satellite in orbit asymmetrically covers one parameter of coverage preferentially over another in a way which is constant relative to the sun, all year round.
A satellite in orbit around the earth, defining an elliptical, retrograde orbit in which ##EQU12## where .OMEGA. is the right ascension of the ascending node and .omega. is the argument of perigee, and wherein an inclination of the orbit is set in a range between 115.degree. and 118.degree..
A satellite in orbit around the earth, defining an elliptical orbit which has orbital parameters to satisfy the equation ##EQU13## wherein neither ##EQU14## where .OMEGA. equals the right ascension of the ascending node and .omega. is the argument of perigee and wherein said orbit is prograde and said satellite in orbit asymmetrically covers one parameter of coverage, preferentially over another in a way which is constant relative to the sun, all year round.
A method of orbiting a satellite around the earth, comprising the steps of obtaining a satellite, and propelling said satellite into an elliptical orbit which has orbital parameters to satisfy the equation ##EQU15## where .OMEGA. is the right ascension of the ascending node, and .omega. is the argument of perigee, and wherein said orbit has characteristics to asymmetrically cover one parameter of coverage preferentially over another in a way which is constant relative to the sun, all year round.
A constellation of satellites in orbit around the earth, each defining an elliptical orbit which has orbital parameters to satisfy the equation ##EQU18## where .OMEGA. is the right ascension of the ascending node, and .omega. is the argument of perigee, and wherein each of said satellites in orbit asymmetrically covers one parameter of coverage preferentially over another in a way which is constant relative to the sun, all year round.
A rocket and satellites, combination comprising:
- a first part, including a rocket which includes boosters for boosting a satellite into orbit, and a inertial guidance unit, said inertial guidance unit including means for propelling said satellite into an elliptical orbit which has orbital parameters to satisfy the equation ##EQU20## where .OMEGA. is the right ascension of the ascending node, and .omega. is the argument of perigee, and wherein said orbit has characteristics to asymmetrically cover one parameter of coverage preferentially over another in a way which is constant relative to the sun, all year round and a satellite in said rocket, said rocket also including means for releasing said satellite into said orbit.
Dependencies are inferred from the claim text.