Elliptical orbit satellite, system, and deployment with controllable coverage characteristics
First Claim
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1. A satellite in orbit around the earth, defining an elliptical orbit which has orbital parameters to satisfy the equation ##EQU10## where Ω
- is the right ascension of the ascending node, and ω
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.
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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.
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Citations
49 Claims
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1. A satellite in orbit around the earth, defining an elliptical orbit which has orbital parameters to satisfy the equation ##EQU10## where Ω
- is the right ascension of the ascending node, and ω
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. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 22)
- is the right ascension of the ascending node, and ω
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16. A satellite in orbit around the earth, defining an elliptical, retrograde orbit in which ##EQU12## where Ω
- is the right ascension of the ascending node and ω
is the argument of perigee, and wherein an inclination of the orbit is set in a range between 115° and
118°
.
- is the right ascension of the ascending node and ω
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17. A satellite in orbit around the earth, defining an elliptical orbit which has orbital parameters to satisfy the equation ##EQU13## wherein neither ##EQU14## where Ω
- equals the right ascension of the ascending node and ω
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. - View Dependent Claims (18, 19, 20, 21)
- equals the right ascension of the ascending node and ω
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23. 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 Ω
- is the right ascension of the ascending node, and ω
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. - View Dependent Claims (24, 25, 26, 27, 28)
- is the right ascension of the ascending node, and ω
-
29. A constellation of satellites in orbit around the earth, each defining an elliptical orbit which has orbital parameters to satisfy the equation ##EQU18## where Ω
- is the right ascension of the ascending node, and ω
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. - View Dependent Claims (30, 31, 32, 33, 34, 35, 36, 37, 38, 39, 40, 41, 42, 43)
- is the right ascension of the ascending node, and ω
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44. 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 Ω
is the right ascension of the ascending node, and ω
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.- View Dependent Claims (45, 46, 47, 48, 49)
Specification