Automated detection and characterization of earth-orbiting satellite maneuvers
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64G-003/00
G01C-021/24
B64G-001/24
출원번호
US-0611201
(2015-01-31)
등록번호
US-9617018
(2017-04-11)
발명자
/ 주소
Wallner, Michele Kubis
Wallner, Richard Nicholas
Cather, Douglas Edward
출원인 / 주소
Rincon Research Corporation
대리인 / 주소
Gifford, Eric A.
인용정보
피인용 횟수 :
0인용 특허 :
3
초록▼
The process validates measurement data that are consistent with the current orbit or allowable maneuvers for Earth-orbiting satellites. The validated data may be processed to detect both large and small maneuvers; large maneuvers that may have been rejected by standard data validation process and sm
The process validates measurement data that are consistent with the current orbit or allowable maneuvers for Earth-orbiting satellites. The validated data may be processed to detect both large and small maneuvers; large maneuvers that may have been rejected by standard data validation process and small maneuvers that may have been missed. Large maneuvers may present as “trends” in the residuals above the noise threshold from multiple sensors. Small maneuvers may present as a deviation from the expected orbit. The OD engine is suitably configured (as per normal operation) to enforce data reduction on any outliers (e.g. 3 sigma). The maneuver estimation routines employ an objective function for selection of maneuver estimates that combines a residual fit to the current orbit and maneuver, orbit consistency and a penalty for validated but unused data (data that is rejected by the OD engine). The combination of enforcing data reduction in the OD engine of validated data while penalizing that reduction biases the estimation routines to select maneuver estimates that fit all or substantially all of the validated data. The maneuver estimation routines also suitably use a center time & duration window to select the maneuver estimate and iterate the process as new measurement data is received to refine the maneuver estimate.
대표청구항▼
1. A method of estimating maneuvers for Earth-orbiting satellites, comprising: acquiring measurement data on an Earth-orbiting satellite from one or more tracking systems;computing measurement residuals as the difference between measured and predicted data in a temporal sliding window for an Earth-o
1. A method of estimating maneuvers for Earth-orbiting satellites, comprising: acquiring measurement data on an Earth-orbiting satellite from one or more tracking systems;computing measurement residuals as the difference between measured and predicted data in a temporal sliding window for an Earth-orbiting satellite;processing the measurement residuals to identify and validate those residuals that are consistent with the current orbit parameters;processing the measurement residuals to identify and validate those residuals that are consistent with an allowable maneuver of the Earth-orbiting satellites and to reject the remaining measurement residuals;defining an objective function including a residual fit component to the current orbit and maneuver estimate, an orbit consistency component and a penalty component for validated measurement residuals rejected by an orbit determination (OD) engine to bias a selection of a maneuver estimate to fit all or substantially all of the validated measurement residuals;processing the validated measurement residuals to detect an occurrence of a maneuver;upon detection of a maneuver, generating a maneuver estimate;running the OD engine with the maneuver estimate on the validated measurement residuals to update the orbit parameters, said OD engine removing validated measurement residuals that present as outliers given the current orbit and maneuver estimate;evaluating the objective function to determine whether the maneuver estimate satisfies a quality metric;updating the maneuver estimate;repeating the steps of running the OD engine, evaluating the objective function and updating the maneuver estimate until the maneuver estimate satisfies the quality metric;applying the maneuver estimate to update the orbit parameters for the Earth-orbiting satellite; andoutputting the orbit parameters and maneuver parameters for the Earth-orbiting satellite. 2. The method of claim 1, wherein the OD engine excludes measurement residuals that lie outside N*sigma from the mean of the measurement residuals where N is a non-zero value and sigma is the standard deviation of the measurement residuals. 3. The method of claim 1, wherein the temporal sliding window spans a period of at least 90 minutes. 4. The method of claim 1, wherein measurement data is provided from a plurality of sensors. 5. The method of claim 1, wherein the validated measurement residuals are generated by separating the measurement residuals into continuous arcs of at least a minimum length;fitting each continuous arc to possible trajectories associated with allowable maneuvers of the Earth-orbiting satellites; andretaining measurement residuals associated with continuous arcs whose fit satisfies a metric. 6. The method of claim 5, wherein the continuous arcs are validated by double differencing the residuals to remove linear and quadratic trends, and then removing residuals that have more than a defined amount of noise with respect to the double-differenced residuals. 7. The method of claim 6, wherein the continuous arcs are validated in both the forward and backwards directions and only the residuals that have more than the defined amount of noise in both directions are removed. 8. The method of claim 5, wherein fitting each continuous arc removes trends associated with allowable maneuvers to flatten the measurement residuals, wherein the flattened residuals that are more than a defined amount of noise are removed. 9. The method of claim 1, wherein the validated measurement residuals are processed to detect the occurrence of large and small maneuvers in which a large maneuver represents a greater deviation from the orbit than the small maneuver by: processing the measurement residuals to determine whether a large maneuver has occurred; andif a large maneuver is not indicated, computing a deviation from the expected orbit to determine whether a small maneuver has occurred. 10. The method of claim 9, wherein measurement residuals are of different types and from multiple sensors, wherein processing to determine the large maneuver comprises, identifying groups of residuals that are trending away from the pre-maneuver orbit,if more than a set percentage of measurement types and sensors have residuals trending away from the pre-maneuver orbit, a large maneuver is detected. 11. The method of claim 9, wherein processing to determine the large maneuver comprises, identifying validated measurement residuals that are more than a defined amount above a mean of the validated residuals. 12. The method of claim 1, wherein generating the maneuver estimate comprises, solving for a maneuver center time and duration, thrust level and direction. 13. The method of claim 1, wherein generating the maneuver estimate comprises, generating a coarse maneuver estimate whose objective function satisfies an initial metric; andrefining the coarse maneuver estimate to provide an objective function that satisfies a final metric. 14. The method of claim 13, wherein the coarse maneuver estimate is generated using a pattern matching technique. 15. The method of claim 13, wherein the coarse maneuver estimate is generated using a stochastic estimation technique. 16. The method of claim 13, wherein if a coarse maneuver estimate whose objective function satisfies the initial metric cannot be found, using a complex maneuver estimation technique to provide the maneuver estimate. 17. The method of claim 1, wherein as new measurement data is received, the process is repeated, incorporating the new measurement data, until a defined amount of post-maneuver measurement data has been included and the results satisfy a quality metric. 18. The method of claim 1, wherein the residual fit component is a metric associated with the orbit determination engine. 19. The method of claim 1, wherein the orbit consistency component is a metric associated with the consistency of the pre- and post-maneuver orbits. 20. The method of claim 1, wherein the rejection penalty component is a metric associated with the amount of measurement data rejected by the current run of OD engine. 21. The method of claim 1, wherein the orbit determination engine is a batch weighted least squares process or an Extended Kalman filter.
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이 특허에 인용된 특허 (3)
Carrico, Jr., John Paul; Craychee, Timothy Adam; Grabowski, III, Henry Casmir, Method and apparatus for initial orbit determination using high-precision orbit propagation and maneuver modeling.
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