IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0986059
(2013-03-27)
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등록번호 |
US-8833702
(2014-09-16)
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발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
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인용정보 |
피인용 횟수 :
1 인용 특허 :
13 |
초록
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An autonomous system for a satellite which calculates collision paths of debris from anywhere within the spheroid around the satellite by using its radar/ladar data and from data on its own orbit derived by onboard sensors such as star, earth and sun sensors or from stored data sent from its ground
An autonomous system for a satellite which calculates collision paths of debris from anywhere within the spheroid around the satellite by using its radar/ladar data and from data on its own orbit derived by onboard sensors such as star, earth and sun sensors or from stored data sent from its ground control station through the satellite's command subsystem. If a collision would be likely, the system calculates the minimum change in the satellite's orbit to avoid such collision and generates and executes commands for firing on-board orbital control thrusters to put the satellite in a suitable avoidance orbit.
대표청구항
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1. A satellite system that can autonomously avoid collision with orbital debris including: An orbital debris tracking device adapted to provide tracking data on a piece of debris;an orbit determination processor adapted to receive said tracking data from said orbital debris tracking device and compu
1. A satellite system that can autonomously avoid collision with orbital debris including: An orbital debris tracking device adapted to provide tracking data on a piece of debris;an orbit determination processor adapted to receive said tracking data from said orbital debris tracking device and compute the orbits of the debris, to produce debris orbital element data, and to compute the satellite's orbital elements from on-board sensors or on-board stored data or both;an ephemeris processor adapted to receive said debris orbital element data from the orbital determination processor, and satellite orbital elements data, and to generate debris ephemeris data for future positions of the debris and future positions of the satellite;a collision calculator adapted to receive the future debris ephemeris data and the future satellite ephemeris data from said ephemeris processor; said collision calculator adapted to compare said future satellite and debris ephemeris data; and to provide an output conclusion, said output conclusion showing whether a collision would or would not occur at some future time between said debris and said satellite;an avoidance orbit processor adapted to receive an output conclusion that a collision is likely to occur and to calculate an avoidance orbit; and processors to create propulsion thruster commands to effect the avoidance orbit and to execute the commands. 2. A satellite system according to claim 1, wherein the orbital tracking device is selected from the group comprising radar, ladar, microwave radar, and optical or microwave recognition; and further comprising an avoidance command processor which receives the data for an avoidance orbit from the avoidance orbit processor, calculates the required commands for the satellite's thruster firings and causes these commands to be executed wherein said orbital tracking device is adapted to provide complete coverage of the spheroid around the satellite for determining the angle, velocity and range of debris from the satellite. 3. A satellite system according to claim 2, wherein a first orbit tracking device is provided for tracking debris having a range of high speeds, relative to the satellite, and a second tracking device is provided for tracking debris having a range of low speeds. 4. A satellite system according to claim 2, wherein a first tracking device is provided for tracking debris having a range of large sizes, and a second tracking device is provided for tracking debris having a range of small sizes. 5. A satellite system according to claim 1, wherein the ephemeris processor is adapted to receive a portion of the debris orbital elements data from the orbital determination processor and a portion of the satellite orbital elements data from on-board sensors or stored on-board data, and wherein the ephemeris processor is adapted to receive a portion of the debris orbital elements data from one or more ground stations and a portion of the satellite orbital elements data from one or more ground stations. 6. A satellite system according to claim 1, wherein the collision calculator determines a collision likelihood for each piece of debris based upon an uncertainty in measurements associated with the orbit, size and/or velocity data associated with the piece of debris. 7. A satellite system according to claim 1, wherein the collision calculator further provides an output conclusion showing whether a collision would occur at some future time between a piece of debris and a possible future position of said satellite after undergoing an orbital change avoidance maneuver. 8. A satellite system according to claim 1, wherein the collision calculator maintains a matrix of orbital maneuver avoidance choices for the satellite, wherein each matrix element includes a risk assessment of debris collision and the amount of on-board fuel required for each maneuver choice and the satellite's operational performance after each possible avoidance maneuver. 9. A satellite system according to claim 1, wherein the collision calculator is adapted to determine if a probability of collision with orbital debris is below a predetermined threshold and to provide at least one conclusion including an ignore conclusion. 10. A satellite system according to claim 1, wherein said satellite avoidance orbit processor is further adapted to choose a solution set of orbital maneuver choices from a matrix depending on one or more satellite operational performance parameters being fully functional for each orbital maneuver choice. 11. A satellite system according to claim 1, wherein said satellite avoidance orbit processor is further adapted to choose a solution set of orbital maneuver choices from a matrix depending on a calculation of the minimum fuel required to achieve the new orbital avoidance solution. 12. A satellite system according to claim 1, wherein the system includes a debris tracking dwell time for performing calculations associated with one or more pieces of debris and prioritizes calculations based upon position and velocity of debris. 13. A satellite system according to claim 9, wherein a satellite system device selected from the group comprising the orbital debris tracking device, orbit determination processor, collision calculator, and act processor, is adapted to ignore all or a portion of the data associated with an ignored object based on the ignore conclusion. 14. A satellite system according to claim 1, wherein the ephemeris processor is further adapted to receive a portion of the debris orbital elements data from the orbital determination processor and a portion of the satellite orbital elements data from the orbital determination processor, and wherein the ephemeris processor is adapted to receive a portion of the debris orbital elements data from one or more ground stations and a portion of the satellite orbital elements data from one or more ground stations. 15. A satellite system to permit a satellite to avoid collision with orbital debris including: orbital debris tracking means adapted to provide streams of tracking data on individual pieces of debris detected in the full spherical envelope around the satellite, orbit determination processing means adapted to receive said tracking data from said orbital tracking means to compute the orbits of the debris, said orbit determination processing means providing debris orbital elements data of the debris including semi-major axis, eccentricity, inclination, right ascension of ascending node, argument of perigee, period, time of perigee and their variances;ephemeris processing means adapted to receive the debris orbital data from the orbital processing means and satellite orbital elements data from on-board sensors or on-board stored data or both, and calculates location ephemeris data for future positions of the debris relative to future positions of the satellite;a collision calculation means adapted to receive the location ephemeris data for a piece of debris and the location ephemeris data for the satellite from said ephemeris processing means, wherein said collision calculation means is adapted to provide a collision conclusion showing whether a collision would or would not occur at a future time between a piece of debris and said satellite;a satellite avoidance orbit processing means adapted to receive output from said collision calculation means and to calculate a minimum change of the satellite's existing orbit to an orbit which avoids collision with said debris; anda calculation means to create propulsion thruster commands to achieve the avoidance orbit and to execute the commands. 16. A satellite system according to claim 15, wherein said orbital debris tracking means includes one or more of the group comprising a radar and a ladar adapted to provide coverage around the satellite for determining the angle, velocity and range of debris from the satellite. 17. A satellite system according to claim 15, further comprising a telemetry system means and a command system means adapted to send and receive the data from the orbit determination processing means to a ground control station having one or more of the ephemeris processing means. 18. A satellite system according to claim 15, further comprising a satellite avoidance commands processing means adapted to receive the data for a minimum change in orbit, to calculate the required commands for the satellite thruster firings and to cause these commands to be executed. 19. A satellite system according to claim 15, wherein the orbital debris tracking means is selected from the group comprising radar, ladar, microwave radar, and optical recognition; wherein the orbital debris tracking means include one or more modes selected from the group comprising pulse mode, continuous mode, and Doppler mode; and wherein the orbital debris tracking means include one or more operating parameters selected from the group comprising pulse width, beam scan, frequency shift, radiated power output and bandwidth. 20. A satellite system according to claim 15, further comprising a first tracking means provided for tracking debris having a range of high speed, relative to the satellite, and a second tracking means for tracking debris having a range of low speeds. 21. A satellite system according to claim 15, further comprising a first tracking means for tracking debris having a range of large sizes, and a second tracking means for tracking debris having a range of small sizes. 22. A satellite system according to claim 15, wherein the ephemeris processing means is adapted to receive a portion of the debris orbital elements data from the orbital determination processing means and a portion of the satellite orbital elements data from on-board sensors or on-board stored data or both, and wherein the ephemeris processing means is adapted to receive a portion of the debris orbital elements data from one or more ground stations and a portion of the satellite orbital elements data from one or more ground control stations. 23. A satellite system according to claim 15, wherein the collision calculation means is adapted to determine a collision likelihood envelope for each piece of debris based upon an uncertainty value of the measurement associated with one or more factors associated with the piece of debris selected from the group comprising the orbit, size and/or velocity data. 24. A satellite system according to claim 15, wherein the collision calculation means is further adapted to provide an output conclusion showing whether a collision would occur at some future time between a piece of debris and a future position of said satellite after the satellite undergoes an orbital change maneuver. 25. A satellite system according to claim 15, wherein the collision calculation means is adapted to maintain a matrix of orbital maneuver choices for the satellite, wherein each matrix element includes a risk assessment of collision and the amount of on-board fuel required for each maneuver choice and the satellite's operational performance after each possible avoidance maneuver. 26. A satellite system according to claim 15, wherein the collision calculation means is adapted to determine if a probability of collision of the orbital debris is below a predetermined threshold and to provide at least one conclusion including an ignore conclusion. 27. A satellite system according to claim 15, wherein said satellite avoidance orbit processing means is further adapted to choose a solution set of orbital maneuver choices from a matrix depending on one or more satellite operational performance parameters being fully functional for each orbital maneuver choice. 28. A satellite system according to claim 15, wherein said satellite avoidance orbit processing means is further adapted to choose a solution set of orbital maneuver choices from a matrix depending on a calculation of the minimum fuel required to achieve the new orbital avoidance solution. 29. A satellite system according to claim 15, wherein the system includes a debris tracking dwell time for performing more detailed measurements associated with one or more pieces of debris and prioritizes avoidance calculations based upon position and velocity of debris. 30. A satellite system according to claim 26, further comprising a satellite system means selected from the group comprising the orbital debris tracking means, orbit determination processing means, collision calculation means, and act processing means, is adapted to ignore all or a portion of the data associated with an ignored object based on the ignore conclusion. 31. A satellite system according to claim 15, wherein the ephemeris processing means is adapted to receive a portion of the debris orbital elements data from the orbital determination processing means and a portion of the satellite orbital elements data from the satellite's computer, and wherein the ephemeris processing means is adapted to receive a portion of the debris orbital elements data from one or more ground stations and a portion of the satellite orbital elements data from one or more ground control stations.
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