IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0411046
(2006-04-25)
|
등록번호 |
US-7689358
(2010-04-23)
|
발명자
/ 주소 |
- Jaeger, Talbot John
- Ngo, Phong David
|
출원인 / 주소 |
- Northrop Grumman Corporation
|
대리인 / 주소 |
Tarolli, Sundheim, Covell & Tummino LLP
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
12 |
초록
▼
A system and method is provided for establishing a substantially delta-V-free three-dimensional atomic satellite cloud cluster. In one embodiment, a satellite cloud cluster system comprises a plurality of satellites maintaining a three-dimensional periodic motion relative to a reference point. The p
A system and method is provided for establishing a substantially delta-V-free three-dimensional atomic satellite cloud cluster. In one embodiment, a satellite cloud cluster system comprises a plurality of satellites maintaining a three-dimensional periodic motion relative to a reference point. The plurality of satellites and the reference point maintain an orbital pattern around a celestial body. The three-dimensional periodic motion is symmetrical about at least two planes that intersect at the reference point.
대표청구항
▼
What is claimed is: 1. A satellite cluster system comprising: a plurality of satellites maintaining a three-dimensional periodic motion relative to a reference point, the plurality of satellites and the reference point maintaining an orbital pattern around a celestial body, the three-dimensional pe
What is claimed is: 1. A satellite cluster system comprising: a plurality of satellites maintaining a three-dimensional periodic motion relative to a reference point, the plurality of satellites and the reference point maintaining an orbital pattern around a celestial body, the three-dimensional periodic motion being symmetrical about at least two planes that intersect at the reference point. 2. The satellite cluster system of claim 1, wherein at least a first portion of the plurality of satellites rotates around the reference point in an elliptical sub-orbit. 3. The satellite cluster system of claim 2, wherein the reference point is a first reference point and wherein at least a second portion of the plurality of satellites rotates around a second reference point in a second elliptical sub-orbit, the second reference point maintaining the orbital pattern around the celestial body and maintaining a substantially constant distance from the first reference point. 4. The satellite cluster system of claim 1, wherein the plurality of satellites are communicatively coupled, such that each satellite of the plurality of satellites adjusts transmission and receiving parameters to account for variations in phase, signal strength, and direction in a respective uplink or downlink signal relative to other satellites in the plurality of satellites. 5. The satellite cluster system of claim 1, wherein first defined orbits of a first portion of the plurality of satellites have values of an inclination and a right ascension of an ascending node (RAAN) that differ from second defined orbits of a second portion of the plurality of satellites. 6. The satellite cluster system of claim 5, wherein each satellite of the first portion of the plurality of satellites has an orbit with a value of argument of perigee and true anomaly that differs from other satellites in the first portion of the plurality of satellites, and each satellite of the second portion of the plurality of satellites has an orbit with a value of argument of perigee and true anomaly that differs from other satellites in the second portion of the plurality of satellites. 7. The satellite cluster system of claim 1, wherein an orbital path of the reference point is a circular orbit. 8. The satellite cluster system of claim 1, further comprising a satellite located at the reference point. 9. The satellite cluster system of claim 1, wherein the three-dimensional periodic motion is formed by minimal impulsive delta-V thrusts by the plurality of satellites from a formation flight orbit. 10. The satellite cluster system of claim 1, wherein at least one satellite in the plurality of satellites has a dedicated function relative to other satellites in the plurality of satellites, and the at least one satellite hands-off the dedicated function to at least one other satellite in the plurality of satellites at least one fixed point on the orbital path. 11. A satellite cluster system comprising: a first plurality of satellites maintaining a first periodic motion relative to a reference point, the reference point maintaining an orbital pattern around a celestial body; a second plurality of satellites maintaining a second periodic motion relative to the reference point; and a third plurality of satellites maintaining a third periodic motion relative to the reference point, the combination of the first, second, and third periodic motions forming a three-dimensional atomic satellite cluster relative to the reference point, and each of the first, second, and third pluralities of satellites being communicatively coupled to each other. 12. The satellite cluster system of claim 11, wherein the first periodic motion defines a first plane, the second periodic motion defines a second plane, and the third periodic motion defines a third plane. 13. The satellite cluster system of claim 12, wherein the reference point is located in the first plane, and wherein the second plane and the third plane are each equidistant from the reference point. 14. The satellite cluster system of claim 11, wherein the orbital pattern is a circular orbit. 15. The satellite cluster system of claim 11, wherein the first plurality of satellites occupy first defined orbits, the second plurality of satellites occupy second defined orbits, the third plurality of satellites occupy third defined orbits, and wherein each of the first defined orbits, the second defined orbits, and the third defined orbits have distinct values of inclination and right ascension of an ascending node (RAAN). 16. The satellite cluster system of claim 11, wherein each one of the satellites in each of the first plurality of satellites, the second plurality of satellites, and the third plurality of satellites occupies a separate orbit with a distinct argument of perigee and a distinct true anomaly, such that each one of the satellites in each of the first plurality of satellites, the second plurality of satellites, and the third plurality of satellites has a uniformly spaced phase-distribution in each of the first periodic motion, the second periodic motion, and the third periodic motion, respectively. 17. The satellite cluster system of claim 16, wherein the sum of the argument of perigee and the true anomaly for each orbit for each one of the plurality of satellites in each of the first plurality of satellites, the second plurality of satellites, and the third plurality of satellites is approximately equal to 360° at an ascending node vector. 18. The satellite cluster system of claim 11, further comprising a satellite located at the reference point. 19. The satellite cluster system of claim 11, wherein the each of the first periodic motion, the second periodic motion, and the third periodic motion are formed by minimal impulsive delta-V thrusts by each of the first plurality of satellites, the second plurality of satellites, and the third plurality of satellites, respectively, from a formation flight orbit. 20. The satellite cluster system of claim 11, wherein each satellite of the first plurality of satellites, the second plurality of satellites, and the third plurality of satellites adjusts transmission and receiving parameters to account for variations in phase, signal strength, and direction in a respective uplink or downlink signal relative to other satellites in each of the first plurality of satellites, the second plurality of satellites, and the third plurality of satellites. 21. The satellite cluster system of claim 11, wherein at least one satellite in each of the first plurality of satellites, the second plurality of satellites, and the third plurality of satellites has at least one dedicated function relative to other satellites in each of the first plurality of satellites, the second plurality of satellites, and the third plurality of satellites, and wherein the dedicated function is handed-off to at least one other satellite in the respective first plurality of satellites, second plurality of satellites, and third plurality of satellites at least one fixed point in the orbital path. 22. A method for establishing a satellite cluster orbit, the method comprising: launching the satellite cluster into a formation-flight to maintain an orbital path about a celestial body; applying minimal delta-V impulse thrusts to a first plurality of satellites of the satellite cluster to set the first plurality of satellites in a first periodic motion relative to a reference point, the reference point orbiting the celestial body at an equal velocity along the same orbital path as the formation flight; applying minimal delta-V impulse thrusts to a second plurality of satellites of the satellite cluster to set the second plurality of satellites in a second periodic motion relative to the reference point; and applying minimal delta-V impulse thrusts to a third plurality of satellites of the satellite cluster to set the third plurality of satellites in a third periodic motion relative to the reference point, the combination of the first, second, and third periodic motions forming a three-dimensional atomic satellite cluster relative to the reference point. 23. The method of claim 22, further comprising forming the first periodic motion into a first elliptical rotation defining a first plane, the reference point occupying the first plane, forming the second periodic motion into a second elliptical rotation defining a second plane, and forming the third periodic motion into a third elliptical rotation defining a third plane, the distance from the reference point to the second plane and from the reference point to the third plane being approximately equal and substantially constant. 24. The method of claim 22, further comprising modifying an inclination and a right ascension of an ascending node (RAAN) of each orbit of the satellites of each of the first plurality of satellites, the second plurality of satellites, and the third plurality of satellites relative to each other. 25. The method of claim 22, further comprising setting the orbital path about the celestial body as a circular orbit. 26. The method of claim 22, further comprising setting a distinct value for argument of perigee and a distinct value for true anomaly for each one of the satellites in each of the first plurality of satellites, the second plurality of satellites, and the third plurality of satellites, such that each one of the satellites in each of the first plurality of satellites, the second plurality of satellites, and the third plurality of satellites has a uniformly spaced phase-distribution in each of the first periodic motion, the second periodic motion, and the third periodic motion, respectively. 27. The method of claim 26, further comprising setting the sum of the argument of perigee and the true anomaly for each orbit of each one of the satellites in each of the first plurality of satellites, second plurality of satellites, and third plurality of satellites approximately equal to 360° at an ascending node vector. 28. The method of claim 22, further comprising establishing one satellite of the satellite cluster as the reference point. 29. The method of claim 22, further comprising handing-off a dedicated functionality of at least one satellite of each of the first plurality of satellites, the second plurality of satellites, and the third plurality of satellites to at least one other satellite of each of the first plurality of satellites, the second plurality of satellites, and the third plurality of satellites at least one fixed point on the orbital path. 30. The method of claim 22, further comprising modifying transmission and receiving parameters for a respective uplink or downlink of each satellite in each of the first plurality of satellites, the second plurality of satellites, and the third plurality of satellites relative to a position of the satellite in the respective first periodic motion, second periodic motion, and third periodic motion.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.