최소 단어 이상 선택하여야 합니다.
최대 10 단어까지만 선택 가능합니다.
다음과 같은 기능을 한번의 로그인으로 사용 할 수 있습니다.
NTIS 바로가기다음과 같은 기능을 한번의 로그인으로 사용 할 수 있습니다.
DataON 바로가기다음과 같은 기능을 한번의 로그인으로 사용 할 수 있습니다.
Edison 바로가기다음과 같은 기능을 한번의 로그인으로 사용 할 수 있습니다.
Kafe 바로가기국가/구분 | United States(US) Patent 등록 |
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국제특허분류(IPC7판) |
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출원번호 | US-0521017 (2014-10-22) |
등록번호 | US-9540122 (2017-01-10) |
발명자 / 주소 |
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출원인 / 주소 |
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대리인 / 주소 |
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인용정보 | 피인용 횟수 : 0 인용 특허 : 4 |
A computing device may detect that a space object has undergone a maneuver and may attempt to calculate a solution to that maneuver based in part on start and stop times and thrust uncertainties associated with the detected maneuver. However, the computing device may sometimes be unable to calculate
A computing device may detect that a space object has undergone a maneuver and may attempt to calculate a solution to that maneuver based in part on start and stop times and thrust uncertainties associated with the detected maneuver. However, the computing device may sometimes be unable to calculate an acceptable solution for a detected maneuver given these initial start and stop times and thrust uncertainties. Thus, the various embodiments provide for a computing device and methods implemented by a processor executing on the device for identifying and calculating a recovery maneuver of a space object when an acceptable solution for a detected maneuver cannot be determined. In the various embodiments, a computing device processor may generate a recovery maneuver based on the detected maneuver, and the processor may adjust the start and stop times and the uncertainty values of the recovery maneuver until an acceptable solution is found.
1. A method of a satellite control system for solving a detected maneuver for a satellite after entering a recovery mode, comprising: determining, by a processor of a computing device of the satellite control system, an initial start time and an initial stop time for the detected maneuver of the sat
1. A method of a satellite control system for solving a detected maneuver for a satellite after entering a recovery mode, comprising: determining, by a processor of a computing device of the satellite control system, an initial start time and an initial stop time for the detected maneuver of the satellite;generating, by the processor, a recovery maneuver for the satellite based on the initial start time and the initial stop time;performing, by the processor, a filtering operation on the recovery maneuver to determine a number of rejected residuals for the recovery maneuver;determining, by the processor, whether the number of rejected residuals of the recovery maneuver exceeds a threshold number of rejected residuals;performing, by the processor, a smoothing operation on the recovery maneuver to calculate a velocity consistency component for each direction of the recover maneuver in response to determining that the number of rejected residuals of the recovery maneuver does not exceed a threshold;determining, by the processor, whether all the calculated velocity consistency components of the recovery maneuver are acceptable after performing the smoothing operation wherein all the calculated velocity consistency components are acceptable when an uncertainty value of the calculated velocity consistency components is at its minimum value; andreporting, by the processor, a solution to the recovery maneuver to the satellite control system in response to determining that all the calculated velocity consistency components of the recovery maneuver are acceptable. 2. The method of claim 1, further comprising: increasing values the initial start time and the initial stop time of the recovery maneuver by the processor in response to determining that the number of rejected residuals of the recovery maneuver exceeds a threshold number of rejected residuals; andrepeating the filtering operation by the processor after increasing the values of the initial start time and the initial stop time. 3. The method of claim 1, further comprising: determining, by the processor, whether a maximum number of attempts has been tried in response to determining that all the calculated velocity consistency components of the recovery maneuver are not acceptable;reporting, by the processor, to the satellite control system that there is no solution to the recovery maneuver in response to determining that the maximum number of attempts has been tried;adjusting, by the processor, an uncertainty value of the calculated velocity components associated with an unacceptable velocity consistency component for each unacceptable velocity consistency component in response to determining that the maximum number of attempts has not been tried; andrepeating the filtering operation by the processor after adjusting an uncertainty value of the calculated velocity components for each unacceptable velocity consistency component. 4. The method of claim 1, wherein determining, by the processor, an initial start time and an initial stop time for the detected maneuver of the satellite comprises: determining, by the processor, when a residual ratio threshold is exceeded;identifying, by the processor, a last good time in a data stream;setting a start time and a stop time of the recovery maneuver by the processor;performing a filtering operation by the processor on the recovery maneuver to identify a number of rejects;determining, by the processor, whether the number of rejects exceeds a threshold number of rejects;determining, by the processor, a period where a thrust is within a threshold of a peak thrust in response to determining that the number of rejects does not exceed the threshold number of rejects; andadjusting, by the processor, the start time and the stop time of the recovery maneuver based on the determined period,wherein tracks of data for the recovery maneuver are part of the data stream. 5. The method of claim 4, further comprising: setting, by the processor, initial values for thrust or time uncertainties of the recovery maneuver;determining, by the processor, whether the thrust or time uncertainties are at their maximum values in response to determining that the number of rejects exceeds the threshold number of rejects;increasing values of the thrust or time uncertainties by the processor in response to determining that the thrust or time uncertainties of the recovery maneuver are not at their maximum values; andrepeating the filtering operation by the processor on the recovery maneuver to identify a number of rejects. 6. The method of claim 5, further comprising: determining, by the processor, whether an analysis start time has been reached in response to determining that the thrust or time uncertainties of the recovery maneuver are at their maximum values;adjusting the start time of the recovery maneuver by the processor in response to determining that the analysis start time has not been reached;repeating the filtering operation by the processor after adjusting the start time of the recovery maneuver; andreporting to the satellite control system, by the processor, that no solution exists for the recovery maneuver in response to determining that the analysis start time has been reached. 7. The method of claim 1, wherein determining an initial start time and an initial stop time for the detected maneuver of the satellite comprises: determining, by the processor, when a residual ratio threshold is exceeded;identifying, by the processor, a previous track that is separated by a certain number of degrees;performing, by the processor, a consistency metric test through a stop time of the previous track;determining, by the processor, whether the previous track passes the consistency metric test; andsetting a start time of the recovery maneuver as the stop time of the previous track and setting the stop time of the recovery maneuver as the start time of a track that most recently failed the consistency metric test by the processor in response to determining that the previous track passed the consistency metric test,wherein tracks of data for the recovery maneuver are not part of a data stream. 8. The method of claim 7, further comprising: determining, by the processor, whether there is another track left to test in response to determining that the previous track did not pass the consistency metric test;reporting, by the processor, that there is no solution to the recovery maneuver in response to determining that there is no track left to test; andselecting, by the processor, another previous track that is separated by the certain number of degrees from the previous track and repeating the consistency metric test operations based on the another previous track in response to determining that there is a track left to test. 9. The method of claim 1, wherein reporting, by the processor, a solution to the recovery maneuver to the satellite control system comprises: minimizing, by the processor, one or more uncertainty values of the calculated velocity consistency components of the recovery maneuver to determine a final solution for the recovery maneuver;computing, by the processor, an objective function value of the final solution; andreporting, by the processor to the satellite control system, the objective function value of the final solution. 10. A method of a satellite control system for solving a detected maneuver after entering a recovery mode, comprising: determining, by a processor of a computing device of the satellite control system, an initial start time and an initial stop time for the detected maneuver of the satellite;generating, by the processor, a recovery maneuver for the satellite based on the initial start time and the initial stop time;performing, by the processor, a filtering operation on the recovery maneuver to determine a number of rejected residuals for the recovery maneuver;determining, by the processor, whether the number of rejected residuals exceeds a threshold number of rejected residuals;performing, by the processor, a smoothing operation on the recovery maneuver to compute a velocity consistency component for each direction component of the recovery maneuver in response to determining that the number of rejected residuals does not exceed a threshold number of rejected residuals;determining, by the processor, whether each velocity consistency component of the recovery maneuver is within a certain tolerance threshold for velocity;adjusting, by the processor, values of one or more velocity uncertainties associated with a velocity consistency component that is not within the certain tolerance threshold for velocity in response to determining that a velocity consistency component is not within the certain tolerance threshold for velocity;repeating the filtering operation by the processor;determining, by the processor, whether the number of rejected residuals exceeds the threshold number of rejected residuals after repeating the filtering operation;repeating the smoothing operation by the processor in response to determining that the number of rejected residuals does not exceed the threshold number of rejected residuals;determining, by the processor, whether each velocity consistency component of the recovery maneuver is within the certain tolerance threshold after repeating the smoothing operation; andreporting, by the processor, a solution to the recovery maneuver to the satellite control system in response to determining that all velocity consistency components of the recovery maneuver are acceptable after repeating the smoothing operation. 11. The method of claim 10, further comprising: determining, by the processor, whether a maximum number of iterations has been reached in response to determining that the number of rejected residuals exceeds the threshold number of rejected residuals;extending, by the processor, the recovery maneuver in response to determining that the maximum number of iterations has been reached; andadjusting, by the processor, values of one or more velocity uncertainties of the recovery maneuver in response to determining that the maximum number of iterations has not been reached. 12. The method of claim 10, further comprising: determining, by the processor, whether a maximum number of iterations of the filtering operation has been performed in response to determining that the number of rejected residuals exceeds the threshold number of rejected residuals after repeating the filtering operation;extending, by the processor, the recovery maneuver in response to determining that the maximum number of iterations of the filtering operation has been performed after repeating the filtering operation; andhalving, by the processor, a step in the velocity uncertainties in response to determining that the maximum number of iterations of the filtering operation has not been performed after repeating the filtering operation; anddetermining, by the processor, that the number of rejected residuals exceeds the threshold number of rejected residuals. 13. The method of claim 10, further comprising: determining, by the processor, whether a maximum number of iterations of the smoothing operation has been performed in response to determining that each velocity consistency component of the recovery maneuver is not within the certain tolerance threshold for velocity after repeating the smoothing operation;extending, by the processor, the recovery maneuver in response to determining that the maximum number of iterations of the smoothing operation has been performed after repeating the smoothing operation; andadjusting, by the processor, values of one or more velocity uncertainties for the recovery maneuver in response to determining that the maximum number of iterations of the smoothing operation has been performed after repeating the smoothing operation. 14. A non-transitory processor readable medium having stored thereon processor executable instructions configured to cause a processor of a computing device of a satellite control system to perform operations comprising: determining an initial start time and an initial stop time for the detected maneuver of a satellite;generating a recovery maneuver for the satellite based on the initial start time and the initial stop time;performing a filtering operation on the recovery maneuver to determine a number of rejected residuals for the recovery maneuver;determining whether the number of rejected residuals of the recovery maneuver exceeds a threshold number of rejected residuals;performing a smoothing operation on the recovery maneuver to calculate a velocity consistency component for each direction of the recover maneuver in response to determining that the number of rejected residuals of the recovery maneuver does not exceed a threshold;determining whether all the calculated velocity consistency components of the recovery maneuver are acceptable after performing the smoothing operation, wherein all the calculated velocity consistency components are acceptable when an uncertainty value of the calculated velocity consistency components is at its minimum value; andreporting a solution to the recovery maneuver to the satellite control system in response to determining that all the calculated velocity consistency components of the recovery maneuver are acceptable. 15. The non-transitory processor readable medium of claim 14, wherein the stored processor executable instructions are configured to cause a processor of a computing device of a satellite control system to perform operations further comprising: increasing values the initial start time and the initial stop time of the recovery maneuver by the processor in response to determining that the number of rejected residuals of the recovery maneuver exceeds a threshold number of rejected residuals; andrepeating the filtering operation by the processor after increasing the values of the initial start time and the initial stop time. 16. The non-transitory processor readable medium of claim 14, wherein the stored processor executable instructions are configured to cause a processor of a computing device of a satellite control system to perform operations further comprising: determining whether a maximum number of attempts has been tried in response to determining that all the calculated velocity consistency components of the recovery maneuver are not acceptable;reporting to the satellite control system that there is no solution to the recovery maneuver in response to determining that the maximum number of attempts has been tried;adjusting an uncertainty value of the calculated velocity components associated with an unacceptable velocity consistency component for each unacceptable velocity consistency component in response to determining that the maximum number of attempts has not been tried; andrepeating the filtering operation by the processor after adjusting an uncertainty value of the calculated velocity components for each unacceptable velocity consistency component. 17. The non-transitory processor readable medium of claim 14, wherein the stored processor executable instructions are configured to cause a processor of a computing device of a satellite control system to perform operations such that determining an initial start time and an initial stop time for the detected maneuver of the satellite comprises: determining when a residual ratio threshold is exceeded;identifying a last good time in a data stream;setting a start time and a stop time of the recovery maneuver;performing a filtering operation on the recovery maneuver to identify a number of rejects;determining whether the number of rejects exceeds a threshold number of rejects;determining a period where a thrust is within a threshold of a peak thrust in response to determining that the number of rejects does not exceed the threshold number of rejects; andadjusting the start time and the stop time of the recovery maneuver based on the determined period,wherein tracks of data for the recovery maneuver are part of the data stream. 18. The non-transitory processor readable medium of claim 17, wherein the stored processor executable instructions are configured to cause a processor of a computing device of a satellite control system to perform operations further comprising: setting initial values for thrust or time uncertainties of the recovery maneuver;determining whether the thrust or time uncertainties are at their maximum values in response to determining that the number of rejects exceeds the threshold number of rejects;increasing values of the thrust or time uncertainties by the processor in response to determining that the thrust or time uncertainties of the recovery maneuver are not at their maximum values; andrepeating the filtering operation by the processor on the recovery maneuver to identify a number of rejects. 19. The non-transitory processor readable medium of claim 18, wherein the stored processor executable instructions are configured to cause a processor of a computing device of a satellite control system to perform operations further comprising: determining whether an analysis start time has been reached in response to determining that the thrust or time uncertainties of the recovery maneuver are at their maximum values;adjusting the start time of the recovery maneuver in response to determining that the analysis start time has not been reached;repeating the filtering operation after adjusting the start time of the recovery maneuver; andreporting to the satellite control system that no solution exists for the recovery maneuver in response to determining that the analysis start time has been reached. 20. The non-transitory processor readable medium of claim 14, wherein the stored processor executable instructions are configured to cause a processor of a computing device of a satellite control system to perform operations such that determining an initial start time and an initial stop time for the detected maneuver of the satellite comprises: determining when a residual ratio threshold is exceeded;identifying a previous track that is separated by a certain number of degrees;performing a consistency metric test through a stop time of the previous track;determining whether the previous track passes the consistency metric test; andsetting a start time of the recovery maneuver as the stop time of the previous track and setting the stop time of the recovery maneuver as the start time of a track that most recently failed the consistency metric test in response to determining that the previous track passed the consistency metric test,wherein tracks of data for the recovery maneuver are not part of a data stream. 21. The non-transitory processor readable medium of claim 20, wherein the stored processor executable instructions are configured to cause a processor of a computing device of a satellite control system to perform operations further comprising: determining whether there is another track left to test in response to determining that the previous track did not pass the consistency metric test;reporting that there is no solution to the recovery maneuver in response to determining that there is no track left to test; andselecting another previous track that is separated by the certain number of degrees from the previous track and repeating the consistency metric test operations based on the another previous track in response to determining that there is a track left to test. 22. The non-transitory processor readable medium of claim 14, wherein the stored processor executable instructions are configured to cause a processor of a computing device of a satellite control system to perform operations such that reporting a solution to the recovery maneuver to the satellite control system comprises: minimizing one or more uncertainty values of the calculated velocity consistency components of the recovery maneuver to determine a final solution for the recovery maneuver;computing an objective function value of the final solution; andreporting to the satellite control system the objective function value of the final solution. 23. A non-transitory processor readable medium having stored thereon processor executable instructions configured to cause a processor of a computing device of a satellite control system to perform operations comprising: determining an initial start time and an initial stop time for the detected maneuver of a satellite;generating a recovery maneuver for the satellite based on the initial start time and the initial stop time;performing a filtering operation on the recovery maneuver to determine a number of rejected residuals for the recovery maneuver;determining whether the number of rejected residuals exceeds a threshold number of rejected residuals;performing a smoothing operation on the recovery maneuver to compute a velocity consistency component for each direction component of the recovery maneuver in response to determining that the number of rejected residuals does not exceed a threshold number of rejected residuals;determining whether each velocity consistency component of the recovery maneuver is within a certain tolerance threshold for velocity;adjusting values of one or more velocity uncertainties associated with a velocity consistency component that is not within the certain tolerance threshold for velocity in response to determining that a velocity consistency component is not within the certain tolerance threshold for velocity;repeating the filtering operation;determining whether the number of rejected residuals exceeds the threshold number of rejected residuals after repeating the filtering operation;repeating the smoothing operation by the processor in response to determining that the number of rejected residuals does not exceed the threshold number of rejected residuals;determining whether each velocity consistency component of the recovery maneuver is within the certain tolerance threshold after repeating the smoothing operation; andreporting a solution to the recovery maneuver to the satellite control system in response to determining that all velocity consistency components of the recovery maneuver are acceptable after repeating the smoothing operation. 24. The non-transitory processor readable medium of claim 23, wherein the stored processor executable instructions are configured to cause a processor of a computing device of a satellite control system to perform operations further comprising: determining whether a maximum number of iterations has been reached in response to determining that the number of rejected residuals exceeds the threshold number of rejected residuals;extending the recovery maneuver in response to determining that the maximum number of iterations has been reached; andadjusting values of one or more velocity uncertainties of the recovery maneuver in response to determining that the maximum number of iterations has not been reached. 25. The non-transitory processor readable medium of claim 23, wherein the stored processor executable instructions are configured to cause a processor of a computing device of a satellite control system to perform operations further comprising: determining whether a maximum number of iterations of the filtering operation has been performed in response to determining that the number of rejected residuals exceeds the threshold number of rejected residuals after repeating the filtering operation;extending the recovery maneuver in response to determining that the maximum number of iterations of the filtering operation has been performed after repeating the filtering operation;halving a step in the velocity uncertainties in response to determining that the maximum number of iterations of the filtering operation has not been performed after repeating the filtering operation; anddetermining that the number of rejected residuals exceeds the threshold number of rejected residuals. 26. The non-transitory processor readable medium of claim 23, wherein the stored processor executable instructions are configured to cause a processor of a computing device of a satellite control system to perform operations further comprising: determining whether a maximum number of iterations of the smoothing operation has been performed in response to determining that each velocity consistency component of the recovery maneuver is not within the certain tolerance threshold for velocity after repeating the smoothing operation;extending the recovery maneuver in response to determining that the maximum number of iterations of the smoothing operation has been performed after repeating the smoothing operation; andadjusting values of one or more velocity uncertainties for the recovery maneuver in response to determining that the maximum number of iterations of the smoothing operation has been performed after repeating the smoothing operation. 27. A computing device of a satellite control system for solving a detected maneuver for a satellite after entering a recovery mode, comprising: a processor configured with processor executable instructions to perform operations comprising:determining an initial start time and an initial stop time for the detected maneuver of a satellite; generating a recovery maneuver for the satellite based on the initial start time and the initial stop time;performing a filtering operation on the recovery maneuver to determine a number of rejected residuals for the recovery maneuver;determining whether the number of rejected residuals of the recovery maneuver exceeds a threshold number of rejected residuals;performing a smoothing operation on the recovery maneuver to calculate a velocity consistency component for each direction of the recover maneuver in response to determining that the number of rejected residuals of the recovery maneuver does not exceed a threshold;determining whether all the calculated velocity consistency components of the recovery maneuver are acceptable after performing the smoothing operation, wherein all the calculated velocity consistency components are acceptable when an uncertainty value of the calculated velocity consistency components is at its minimum value; andreporting a solution to the recovery maneuver to the satellite control system in response to determining that all the calculated velocity consistency components of the recovery maneuver are acceptable. 28. The computing device of claim 27, wherein the processor is configured with processor executable instructions to perform operations further comprising: increasing values the initial start time and the initial stop time of the recovery maneuver by the processor in response to determining that the number of rejected residuals of the recovery maneuver exceeds a threshold number of rejected residuals; andrepeating the filtering operation by the processor after increasing the values of the initial start time and the initial stop time. 29. The computing device of claim 27, wherein the processor is configured with processor executable instructions to perform operations further comprising: determining whether a maximum number of attempts has been tried in response to determining that all the calculated velocity consistency components of the recovery maneuver are not acceptable;reporting to the satellite control system that there is no solution to the recovery maneuver in response to determining that the maximum number of attempts has been tried;adjusting an uncertainty value of the calculated velocity components associated with an unacceptable velocity consistency component for each unacceptable velocity consistency component in response to determining that the maximum number of attempts has not been tried; andrepeating the filtering operation by the processor after adjusting an uncertainty value of the calculated velocity components for each unacceptable velocity consistency component. 30. The computing device of claim 27, wherein the processor is configured with processor executable instructions to perform operations such that determining an initial start time and an initial stop time for the detected maneuver of the satellite comprises: determining when a residual ratio threshold is exceeded;identifying a last good time in a data stream;setting a start time and a stop time of the recovery maneuver;performing a filtering operation on the recovery maneuver to identify a number of rejects;determining whether the number of rejects exceeds a threshold number of rejects;determining a period where a thrust is within a threshold of a peak thrust in response to determining that the number of rejects does not exceed the threshold number of rejects; andadjusting the start time and the stop time of the recovery maneuver based on the determined period,wherein tracks of data for the recovery maneuver are part of the data stream. 31. The computing device of claim 30, wherein the processor is configured with processor executable instructions to perform operations further comprising: setting initial values for thrust or time uncertainties of the recovery maneuver;determining whether the thrust or time uncertainties are at their maximum values in response to determining that the number of rejects exceeds the threshold number of rejects;increasing values of the thrust or time uncertainties by the processor in response to determining that the thrust or time uncertainties of the recovery maneuver are not at their maximum values; andrepeating the filtering operation by the processor on the recovery maneuver to identify a number of rejects. 32. The computing device of claim 31, wherein the processor is configured with processor executable instructions to perform operations further comprising: determining whether an analysis start time has been reached in response to determining that the thrust or time uncertainties of the recovery maneuver are at their maximum values;adjusting the start time of the recovery maneuver in response to determining that the analysis start time has not been reached;repeating the filtering operation after adjusting the start time of the recovery maneuver; andreporting to the satellite control system that no solution exists for the recovery maneuver in response to determining that the analysis start time has been reached. 33. The computing device of claim 27, wherein the processor is configured with processor executable instructions to perform operations such that determining an initial start time and an initial stop time for the detected maneuver of the satellite comprises: determining when a residual ratio threshold is exceeded;identifying a previous track that is separated by a certain number of degrees;performing a consistency metric test through a stop time of the previous track;determining whether the previous track passes the consistency metric test; andsetting a start time of the recovery maneuver as the stop time of the previous track and setting the stop time of the recovery maneuver as the start time of a track that most recently failed the consistency metric test in response to determining that the previous track passed the consistency metric test,wherein tracks of data for the recovery maneuver are not part of a data stream. 34. The computing device of claim 33, wherein the processor is configured with processor executable instructions to perform operations further comprising: determining whether there is another track left to test in response to determining that the previous track did not pass the consistency metric test;reporting that there is no solution to the recovery maneuver in response to determining that there is no track left to test; andselecting another previous track that is separated by the certain number of degrees from the previous track and repeating the consistency metric test operations based on the another previous track in response to determining that there is a track left to test. 35. The computing device of claim 27, wherein the processor is configured with processor executable instructions to perform operations such that reporting a solution to the recovery maneuver to the satellite control system comprises: minimizing one or more uncertainty values of the calculated velocity consistency components of the recovery maneuver to determine a final solution for the recovery maneuver;computing an objective function value of the final solution; andreporting to the satellite control system the objective function value of the final solution. 36. A computing device of a satellite control system for solving a detected maneuver for a satellite after entering a recovery mode, comprising: a processor configured with processor executable instructions to perform operations comprising: an initial start time and an initial stop time for the detected maneuver of a satellite;generating a recovery maneuver for the satellite based on the initial start time and the initial stop time;performing a filtering operation on the recovery maneuver to determine a number of rejected residuals for the recovery maneuver;determining whether the number of rejected residuals exceeds a threshold number of rejected residuals;performing a smoothing operation on the recovery maneuver to compute a velocity consistency component for each direction component of the recovery maneuver in response to determining that the number of rejected residuals does not exceed a threshold number of rejected residuals;determining whether each velocity consistency component of the recovery maneuver is within a certain tolerance threshold for velocity;adjusting values of one or more velocity uncertainties associated with a velocity consistency component that is not within the certain tolerance threshold for velocity in response to determining that a velocity consistency component is not within the certain tolerance threshold for velocity;repeating the filtering operation;determining whether the number of rejected residuals exceeds the threshold number of rejected residuals after repeating the filtering operation;repeating the smoothing operation by the processor in response to determining that the number of rejected residuals does not exceed the threshold number of rejected residuals;determining whether each velocity consistency component of the recovery maneuver is within the certain tolerance threshold after repeating the smoothing operation; andreporting a solution to the recovery maneuver to the satellite control system in response to determining that all velocity consistency components of the recovery maneuver are acceptable after repeating the smoothing operation. 37. The computing device of claim 36, wherein the processor is configured with processor executable instructions to perform operations further comprising: determining whether a maximum number of iterations has been reached in response to determining that the number of rejected residuals exceeds the threshold number of rejected residuals;extending the recovery maneuver in response to determining that the maximum number of iterations has been reached; andadjusting values of one or more velocity uncertainties of the recovery maneuver in response to determining that the maximum number of iterations has not been reached. 38. The computing device of claim 36, wherein the processor is configured with processor executable instructions to perform operations further comprising: determining whether a maximum number of iterations of the filtering operation has been performed in response to determining that the number of rejected residuals exceeds the threshold number of rejected residuals after repeating the filtering operation;extending the recovery maneuver in response to determining that the maximum number of iterations of the filtering operation has been performed after repeating the filtering operation;halving a step in the velocity uncertainties in response to determining that the maximum number of iterations of the filtering operation has not been performed after repeating the filtering operation; anddetermining that the number of rejected residuals exceeds the threshold number of rejected residuals. 39. The computing device of claim 36, wherein the processor is configured with processor executable instructions to perform operations further comprising: determining whether a maximum number of iterations of the smoothing operation has been performed in response to determining that each velocity consistency component of the recovery maneuver is not within the certain tolerance threshold for velocity after repeating the smoothing operation;extending the recovery maneuver in response to determining that the maximum number of iterations of the smoothing operation has been performed after repeating the smoothing operation; andadjusting values of one or more velocity uncertainties for the recovery maneuver in response to determining that the maximum number of iterations of the smoothing operation has been performed after repeating the smoothing operation.
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