CN109344084B - Spacecraft test data post interpretation and criterion verification method - Google Patents
Spacecraft test data post interpretation and criterion verification method Download PDFInfo
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Abstract
The invention relates to a spacecraft test data post interpretation and criterion verification method, which comprises the following steps: s1, determining the power-on time of the spacecraft corresponding to the historical data, extracting the historical data, and simulating the extracted historical data into input information for later interpretation or input information for criterion verification; and S2, inputting the simulated input information of the after-interpretation or the simulated input information verified by the criterion into an automatic interpretation system for interpretation. The spacecraft test data post interpretation and criterion verification method realizes interpretation and criterion verification of historical data in a database.
Description
Technical Field
The invention belongs to the technical field of spacecraft electrical performance comprehensive test, particularly belongs to the field of spacecraft test application, and particularly relates to a spacecraft test data post interpretation and criterion verification method.
Background
During the comprehensive test of the ground electrical performance of the spacecraft and the in-orbit flight process, a large amount of data can be downloaded, and the judgment of the correctness of the downloaded parameters is a necessary means for ensuring the sufficiency and the validity of the test of the spacecraft and ensuring the success of model tasks. After the data are downloaded, the data are processed by a ground comprehensive test system, and the judgment of the data correctness can be obtained in real time by means of a test data automatic interpretation system, and finally the data become historical test data in a database and historical test data interpretation conclusion information.
At present, an automatic interpretation system for test data is applied in a large scale, so that real-time interpretation of spacecraft download data becomes possible. However, the historical data existing in the database cannot be accurately interpreted by the conventional automatic interpretation system. Meanwhile, the automatic interpretation criterion verification has no effective tool, so that the criterion verification period is longer.
Disclosure of Invention
The invention aims to provide a spacecraft test data post interpretation and criterion verification method, which is used for realizing interpretation and criterion verification of historical data in a database.
In order to achieve the above object, the present invention provides a spacecraft test data post interpretation and criterion verification method, which comprises:
s1, determining the power-on time of the spacecraft corresponding to the historical data, extracting the historical data, and simulating the extracted historical data into input information for later interpretation or input information for criterion verification;
and S2, inputting the simulated input information of the after-interpretation or the simulated input information verified by the criterion into an automatic interpretation system for interpretation.
According to an aspect of the present invention, the step S1 includes:
s11, inputting the starting time and/or the ending time of the time period needing to be interpreted afterwards by the user;
s12, according to the pre-configured spacecraft power on/off instruction information, finding out the corresponding time of the latest power on instruction before the input starting time from historical data, and recording the time as spacecraft power on time;
and S13, taking the historical data between the power-on time of the spacecraft and the termination time input by the user, which is obtained in the step S12, as input information of post interpretation or input information of criterion verification.
According to an aspect of the present invention, in the step S2, the input information obtained in the step S13 is used as analog data, the interpretation rate of the analog data is set, and the input data is inputted to an automated interpretation system for interpretation.
According to an aspect of the present invention, in step S11, if the user only inputs the termination time, the time corresponding to the latest power-on command before the termination time input by the user is found from the history data, and the time is recorded as the power-on time of the spacecraft.
According to one aspect of the invention, if the user only inputs the starting time, finding out the time corresponding to the first power-off instruction after the power-on time of the spacecraft from the historical data, and recording the time as the power-off time of the spacecraft;
and taking historical data between the power-on time of the spacecraft and the power-off time of the spacecraft as input information for later interpretation or input information for criterion verification.
According to one aspect of the invention, when the spacecraft test data is subjected to criterion verification, if a user only selects to verify the test data within the power-on and power-off range of the spacecraft once, if the user inputs the termination time which is earlier than the inquired power-off time of the spacecraft or the power-off time of the spacecraft cannot be inquired, historical data between the obtained power-on time and the termination time of the spacecraft is used as input information for criterion verification.
According to one aspect of the invention, if the user inputs the termination time, and the termination time is not earlier than the inquired power-off time of the spacecraft, historical data between the power-on time of the spacecraft and the power-off time of the spacecraft is used as input information for criterion verification.
According to one scheme of the invention, the spacecraft test data post interpretation and criterion verification method supports effective extraction of spacecraft historical data, and the extracted test data can simulate data downloaded by a spacecraft in real time and can conveniently and effectively adjust the speed of the simulated data. The existing automatic interpretation system can be utilized to interpret the correctness of the historical data. The criterion of the automatic interpretation system can be verified in correctness by means of historical data, and the effect can be checked by repeatedly adjusting, so that the interpretation verification efficiency of the automatic interpretation system is greatly improved.
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In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a flow chart that schematically illustrates a method for post-interpretation of spacecraft test data in accordance with the present invention;
FIG. 2 is a flow chart that schematically illustrates a method for verifying spacecraft measurement data criteria, in accordance with the present invention.
Detailed Description
The description of the embodiments of this specification is intended to be taken in conjunction with the accompanying drawings, which are to be considered part of the complete specification. In the drawings, the shape or thickness of the embodiments may be exaggerated and simplified or conveniently indicated. Further, the components of the structures in the drawings are described separately, and it should be noted that the components not shown or described in the drawings are well known to those skilled in the art.
Any reference to directions and orientations to the description of the embodiments herein is merely for convenience of description and should not be construed as limiting the scope of the invention in any way. The following description of the preferred embodiments refers to combinations of features which may be present independently or in combination, and the present invention is not particularly limited to the preferred embodiments. The scope of the invention is defined by the claims.
The spacecraft test data post interpretation and criterion verification method comprises the steps of S1, determining spacecraft power-on time corresponding to historical data, extracting the historical data, and simulating the extracted historical data into input information for post interpretation or input information for criterion verification;
and S2, inputting the simulated input information of the after-interpretation or the simulated input information verified by the criterion into an automatic interpretation system for interpretation.
The following respectively describes the spacecraft test data post-interpretation method and the spacecraft test criterion verification in detail.
As shown in fig. 2, the spacecraft test data post interpretation method of the present invention includes the following steps:
step one, a user inputs the starting time and/or the ending time of a time period needing to be subjected to postero-interpretation. And if the user does not input the starting time or the ending time, prompting the user to reselect the time range and then continuing the step one.
And step two, according to the spacecraft power-on and power-off instruction information configured by the user, finding out the time corresponding to the latest power-on instruction before the starting time input by the user from the historical data, and recording the time as the spacecraft power-on time. If the user does not input the starting time (only the ending time is input), the time corresponding to the latest power-on command before the ending time input by the user is found from the historical data, and the time is recorded as the power-on time of the spacecraft. If the power-on time of the spacecraft cannot be obtained through query in the step, prompting the user to reselect the time range and continuing the step I.
And step three, taking the historical data between the powering-on time of the spacecraft and the termination time input by the user, which is obtained in the step two, as input information of after-event interpretation. And if the user does not input the termination time (only the starting time is input), finding out the time corresponding to the first power-off instruction after the power-on time of the spacecraft obtained in the step two from the historical data, recording the time as the power-off time of the spacecraft, and taking the historical data between the power-on time of the spacecraft obtained in the step two and the power-off time of the spacecraft as the input information of the after-interpretation. And if the user does not input the termination time and cannot inquire the outage time of the spacecraft, prompting the user to reselect the time range and continuing the step one.
And step four, the input information obtained in the step three is used as analog data, the analog data is input into the automatic interpretation system according to the interpretation rate of the analog data set by the user, and the output interpretation conclusion is received from the automatic interpretation system and is provided for the user to perform post interpretation.
The spacecraft test data criterion verification method comprises the following steps:
step one, a user inputs the starting time and/or the ending time of a time period needing to be subjected to postero-interpretation. And if the user does not input the starting time or the ending time, prompting the user to reselect the time range and then continuing the step one.
And step two, if the user does not select to verify the data within the power on/off range once, finding out the time corresponding to the latest power on instruction before the initial time input by the user from the historical data according to the power on/off instruction information of the spacecraft configured by the user, and recording the time as the power on time of the spacecraft.
If the user does not input the starting time (only the ending time is input), finding out the time corresponding to the latest power-on command before the ending time input by the user from the historical data, and recording the time as the power-on time of the spacecraft. If the power-on time of the spacecraft cannot be obtained through query in the step, prompting the user to reselect the time range and continuing the step I.
Step three, historical data between the powering-on time of the spacecraft and the termination time input by the user obtained in the step two is used as input information for criterion verification; and if the user does not input the termination time (only the starting time is input), finding out the time corresponding to the first power-off instruction after the power-on time of the spacecraft obtained in the step two from the historical data, recording the time as the power-off time of the spacecraft, and taking the historical data between the power-on time of the spacecraft obtained in the step two and the power-off time of the spacecraft as input information verified by the criterion. And if the user does not input the termination time and cannot inquire the outage time of the spacecraft, prompting the user to reselect the time range and continuing the step one.
And step four, the input information obtained in the step three is used as analog data, the analog data is input into the automatic interpretation system according to the interpretation rate of the analog data set by the user, and the output interpretation conclusion is received from the automatic interpretation system and is provided for the user to carry out criterion verification.
If the user selects to verify the data in the power on/off range only once, after the step one, according to the spacecraft power on/off instruction information configured by the user, finding out the time corresponding to the latest power on instruction before the starting time input by the user from the historical data, and recording the time as the spacecraft power on time. If the starting time is not input by the user, finding out the time corresponding to the latest power-on command before the ending time input by the user from the historical data, and recording the time as the power-on time of the spacecraft. If the power-on time of the spacecraft cannot be obtained through query in the step, prompting the user to reselect the time range and continuing the step I.
If the user does not input the termination time, finding out the time corresponding to the first power-off instruction after the power-on time of the spacecraft from the historical data, recording the time as the power-off time of the spacecraft, and taking the historical data between the power-on time of the spacecraft and the power-off time of the spacecraft obtained as input information for criterion verification.
And if the user inputs the termination time which is earlier than the inquired spacecraft power-off time or the spacecraft power-off time cannot be inquired, using the obtained historical data between the spacecraft power-on time and the termination time as input information for criterion verification.
And if the user inputs the termination time which is not earlier than the inquired power-off time of the spacecraft, taking historical data between the power-on time of the spacecraft and the power-off time of the spacecraft as input information for criterion verification.
And if the user does not input the termination time and cannot inquire the outage time of the spacecraft, prompting the user to reselect the time range and continuing the step one.
And finally, the obtained input information is used as analog data, the analog data is input into the automatic interpretation system according to the interpretation rate of the analog data set by the user, and the output interpretation conclusion is received from the automatic interpretation system and is provided for the user to carry out criterion verification.
The method selects data which can be used for spacecraft test data post interpretation and criterion verification from historical data according to the characteristics that spacecraft parameters start to change states along with the power-up of the whole spacecraft and the states are cleared after the power-off, and provides a corresponding post interpretation and criterion verification method. The following takes parameters T001 and T002 as examples to specifically describe the spacecraft test data post interpretation and criterion verification method of the present invention.
When the parameter T001 is subjected to post interpretation, the range of the historical data needing to be input into the automatic interpretation system is determined according to the starting time T1 and the ending time T2 of the user input time period. When the user sets T1 and T2, the method of the invention finds out the time T1 'corresponding to the latest power-on command before T1 from the historical data according to the power-on and power-off command information of the spacecraft configured by the user, and takes the historical data between T1' and T2 as the input information of post-interpretation. When the user sets T1 but not T2, the method of the invention finds out the time T1' corresponding to the latest power-on command before T1 from the historical data and finds out the time T2' corresponding to the first power-off command after T1' from the historical data according to the power-on and power-off command information of the spacecraft configured by the user, and takes all data from T1' to T2' as the input information of the after-event interpretation. When the user has set only T2 but not T1, the time T1 'corresponding to the latest power-on command at T2 is found from the history data, and the history data between T1' to T2 is used as the input information for the after-call interpretation. When the user does not set the T1 or the T2, or the T1 'and the T2' which are needed to be used cannot be inquired, the user is prompted to reselect the time range.
When criterion verification is carried out on the parameter T002, if the user does not set data in a power-on and power-off range which is verified once, the historical data range which needs to be input into the automatic interpretation system is determined according to the starting time T1 and the ending time T2 of the user input time period. When the user sets T1 and T2, the method of the invention finds out the time T1 'corresponding to the latest power-on command before T1 from the historical data according to the power-on and power-off command information of the spacecraft configured by the user, and takes the historical data between T1' and T2 as the input information of post-interpretation. When the user sets T1 but not T2, the method of the invention finds out the time T1' corresponding to the latest power-on command before T1 from the historical data and finds out the time T2' corresponding to the first power-off command after T1' from the historical data according to the power-on and power-off command information of the spacecraft configured by the user, and takes all data from T1' to T2' as the input information of the after-event interpretation.
When the user has set only T2 but not T1, the time T1 'corresponding to the latest power-on command at T2 is found from the history data, and the history data between T1' to T2 is used as the input information for the after-call interpretation. If the user sets the data within the power-on and power-off range which is verified once, determining the range of the historical data which needs to be input into the automatic interpretation system according to the starting time T1 and the ending time T2 of the time period input by the user. When the user sets T1 and T2, the method of the invention finds out the time T1 'corresponding to the latest power-on command before T1 from the historical data according to the power-on and power-off command information of the spacecraft configured by the user, and finds out the time T2' corresponding to the first power-off command after T1 'from the historical data, if T2< T2' or T2 'does not exist, the historical data between T1' and T2 is used as the input information for criterion verification. If T2 > T2', historical data between T1' and T2' are used as input information for criterion verification.
When the user sets T1 but not T2, the method of the invention finds out the time T1' corresponding to the latest power-on command before T1 from the historical data and finds out the time T2' corresponding to the first power-off command after T1' from the historical data according to the power-on and power-off command information of the spacecraft configured by the user, and takes all data from T1' to T2' as input information for checking the criterion. When the user only sets T2 but not T1, finding out the time T1 'corresponding to the latest power-on command of T2 from the historical data, and finding out the time T2' corresponding to the first power-off command after T1 'from the historical data, if T2< T2', using the historical data between T1 'and T2 as input information for criterion verification, and if 1T2 > 2', using the historical data between T1 'and T2' as input information for criterion verification. When the user does not set the T1 or the T2, or the T1 'and the T2' which are needed to be used cannot be inquired, the user is prompted to reselect the time range.
The spacecraft test data post interpretation and criterion verification method provided by the invention has the advantages that the automatic interpretation level of spacecraft download data is improved, the analysis and processing capacity of the spacecraft download data is improved, the automatic interpretation processing of historical data consistent with real-time data is supported, and the efficiency of automatic interpretation criterion verification is effectively improved. The method supports effective extraction of spacecraft historical data, and the extracted test data can simulate data downloaded by the spacecraft in real time and can conveniently and effectively adjust the speed of the simulated data. The existing automatic interpretation system can be utilized to interpret the correctness of the historical data. The criterion of the automatic interpretation system can be verified in correctness by means of historical data, and the effect can be checked by repeatedly adjusting, so that the interpretation verification efficiency of the automatic interpretation system is greatly improved.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (5)
1. A spacecraft test data post interpretation and criterion verification method comprises the following steps:
s1, determining the power-on time of the spacecraft corresponding to the historical data, extracting the historical data, and simulating the extracted historical data into input information for later interpretation or input information for criterion verification;
the step S1 includes:
s11, inputting the starting time and the ending time of the time period needing to be interpreted afterwards by the user;
s12, according to the pre-configured spacecraft power on/off instruction information, finding out the corresponding time of the latest power on instruction between the input starting times from historical data, and recording the time as the spacecraft power on time;
s13, taking the historical data between the power-on time of the spacecraft and the termination time input by the user, which are obtained in the step S12, as input information of post interpretation or input information of criterion verification;
s2, inputting the simulated input information of the after-interpretation or the simulated input information of the criterion verification into an automatic interpretation system for interpretation;
in step S2, the input information obtained in step S13 is used as analog data, and the interpretation rate of the analog data is set and input to an automated interpretation system for interpretation.
2. A spacecraft test data post-interpretation and criterion verification method according to claim 1, wherein in the step S11, if the user only inputs the termination time, the time corresponding to the latest power-on command before the termination time input by the user is found from the historical data and is recorded as the spacecraft power-on time.
3. The method for judging and verifying spacecraft test data after event according to claim 1, wherein if the user only inputs the starting time, the time corresponding to the first power-off command after the power-on time of the spacecraft is found from the historical data and is marked as the power-off time of the spacecraft;
and taking historical data between the power-on time of the spacecraft and the power-off time of the spacecraft as input information for later interpretation or input information for criterion verification.
4. The method for judging and verifying the spacecraft test data after the event according to claim 1, wherein when the spacecraft test data is verified, if a user only selects to verify the test data within the power on and off range of the spacecraft once, if the user inputs the termination time which is earlier than the queried power off time of the spacecraft or the power off time of the spacecraft cannot be queried, the obtained historical data between the power on time of the spacecraft and the termination time is used as the input information for verifying the criterion.
5. The method for judging and verifying spacecraft test data after fact according to claim 4, wherein if a user inputs a termination time which is not earlier than the queried power-off time of the spacecraft, historical data between the power-on time of the spacecraft and the power-off time of the spacecraft is used as input information for verifying the criterion.
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| CN103218451A (en) * | 2013-04-27 | 2013-07-24 | 北京空间飞行器总体设计部 | Automatic spacecraft test data interpreting method |
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