CN115583350A - Method, device, equipment and medium for identifying performance abnormity of aircraft hydraulic system - Google Patents
Method, device, equipment and medium for identifying performance abnormity of aircraft hydraulic system Download PDFInfo
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Abstract
The application discloses a method, a device, equipment and a medium for identifying performance abnormity of an aircraft hydraulic system, and relates to the technical field of abnormity identification of the aircraft hydraulic system. The method comprises the steps of obtaining historical flight parameter data of a hydraulic system of a target aircraft; extracting the characteristics of the historical flight parameter data of the target aircraft hydraulic system to obtain the flight parameter characteristic data; acquiring a composite distance model between the flight parameter characteristic data of any two flight frames of the target aircraft based on the flight parameter characteristic data; based on the composite distance model, obtaining an associated distance model of the flight parameter characteristic data between a certain flight frame of the target aircraft and the rest flight frames; and identifying the abnormal frequency of the target aircraft hydraulic system based on the correlation distance model. Through the technical scheme, whether the hydraulic system of the target aircraft is abnormal or not can be identified more accurately, and the hydraulic system of the target aircraft can be maintained more timely and accurately.
Description
Technical Field
The application relates to the technical field of abnormity identification of an aircraft hydraulic system, in particular to a method, a device, equipment and a medium for identifying performance abnormity of the aircraft hydraulic system.
Background
The aircraft hydraulic system is used as an important energy transfer system and has an important function of driving movable parts on an aircraft, the use availability of the aircraft is reduced if the performance of the aircraft is degraded and the failure occurs, and major accidents occur if the performance of the aircraft is degraded and the failure occurs, so that the normal operation of the aircraft hydraulic system is related to the safe use of the aircraft, and the aircraft hydraulic system needs to be detected and maintained in time in order to identify whether the performance of the aircraft hydraulic system is normal.
At present, the state detection and maintenance of the aircraft hydraulic system are generally carried out in a mode of combining flying parameter data analysis after flying and preventive maintenance, and the problems of the aircraft hydraulic system are found through manual interpretation of the flying parameter data so as to provide decision basis for flying in the next wave.
However, in the prior art, the performance degradation trend of the aircraft hydraulic system cannot be judged manually, so that whether the aircraft hydraulic system is abnormal or not cannot be accurately identified.
Disclosure of Invention
The application mainly aims to provide a method, a device, equipment and a medium for identifying performance abnormity of an aircraft hydraulic system, and aims to solve the technical problem that in the prior art, the performance decline trend of the aircraft hydraulic system cannot be judged manually, so that whether the aircraft hydraulic system is abnormal or not cannot be identified accurately.
In order to achieve the above object, a first aspect of the present application provides a method for identifying performance abnormality of an aircraft hydraulic system, the method including:
acquiring historical flight parameter data of a hydraulic system of a target aircraft; the historical flight parameter data comprises state data of the hydraulic system of the target aircraft in a plurality of flight legs;
extracting the characteristics of the historical flight parameter data of the target aircraft hydraulic system to obtain the flight parameter characteristic data; the flight parameter characteristic data is used for representing the performance of the target aircraft hydraulic system;
acquiring a composite distance model between the flight parameter characteristic data of any two flight frames of the target aircraft based on the flight parameter characteristic data; the composite distance model is used for representing the difference between the same flight parameter characteristic data of any two flight frames of the target aircraft;
based on the composite distance model, obtaining an associated distance model of the flight parameter characteristic data between a certain flight frame of the target aircraft and the rest flight frames; the correlation distance model is used for evaluating the similarity of the same flight parameter characteristic data between a certain flight frame number and the rest flight frame numbers of the target aircraft;
and identifying the abnormal frequency of the target aircraft hydraulic system based on the correlation distance model.
Optionally, the identifying, based on the correlation distance model, the number of abnormal occurrences of the target aircraft hydraulic system comprises:
obtaining a standard deviation of correlation distances among the flight parameter feature data of a plurality of times of the target aircraft based on the correlation distance model;
and identifying the abnormal frequency of the target aircraft hydraulic system based on the standard deviation.
Optionally, the identifying, based on the standard deviation, the number of anomalies of the target aircraft hydraulic system includes:
presetting an abnormal judgment threshold value based on the standard deviation; the preset abnormal judgment threshold comprises H times of standard deviation; wherein H is a positive number;
and identifying the abnormal frequency of the target aircraft hydraulic system based on the abnormal judgment threshold value.
Optionally, the identifying, based on the abnormality judgment threshold, the number of times of abnormality of the target aircraft hydraulic system includes:
and if the associated distance corresponding to a certain flight number of the target aircraft is greater than the abnormal judgment threshold value, judging that the flight number is an abnormal number.
Optionally, after the step of determining that a certain number of the flight frames of the target aircraft is an abnormal number if the associated distance corresponding to the certain number of the flight frames is greater than the abnormal determination threshold, the method further includes:
checking whether a hydraulic system of the target aircraft corresponding to the abnormal frame number is normal or not;
if the hydraulic system of the target aircraft is abnormal, setting a treatment suggestion instruction; wherein the treatment recommendation command comprises a command to change a hydraulic system of the target aircraft from abnormal to normal;
if the hydraulic system of the target aircraft is normal, setting a reset instruction; wherein the reset instruction comprises an instruction to adjust the anomaly determination threshold.
Optionally, the identifying, based on the correlation distance model, the number of anomalies of the target aircraft hydraulic system includes:
obtaining a variation trend graph of the correlation distance of the target aircraft flying frame number based on the correlation distance model;
and identifying the abnormal number of the target aircraft hydraulic system based on the change trend graph of the associated distance of the target aircraft flight number.
Optionally, the performing feature extraction on the historical flight parameter data of the target aircraft hydraulic system to obtain flight parameter feature data includes:
storing historical flight parameter data of the target aircraft hydraulic system;
classifying the stored historical flight parameter data according to different data types;
respectively extracting feature matrixes of the classified historical flight parameter data;
and carrying out normalization processing on the feature matrix of the historical flight parameter data to obtain the flight parameter feature data.
Optionally, the obtaining a composite distance model between the flight parameter feature data of any two flight frames of the target aircraft based on the flight parameter feature data includes:
obtaining a composite distance model between the flight parameter characteristic data of any two flight times of the target aircraft through the following relational expression:
r(i，j)＝d(q i ，c j )+min{r(i-1，j-1)，r(i-1，j)，r(i，j-1)}
wherein r (i, j) represents a composite distance model between the ith and jth stands of the target aircraft, and d (q) i ，c j ) Representing q on the ith rack of the target aircraft i Point and c on the jth frame j The Euclidean distance between points, min { } represents the minimum value selected;
the obtaining of the associated distance model of the flight parameter feature data between a certain flight frame of the target aircraft and the rest of the flight frames based on the composite distance model includes:
obtaining an association distance model of the flight parameter characteristic data between a certain flight frame of the target aircraft and the rest flight frames through the following relational expression:
the cost represents an associated distance model of flight parameter characteristic data between a certain flight frame number and the rest flight frame numbers of the target aircraft, and N represents the total number of the historical flight frame numbers of the target aircraft.
In a second aspect, the present application provides an apparatus for identifying performance anomalies of an aircraft hydraulic system, the apparatus including:
the acquisition module is used for acquiring historical flight parameter data of a hydraulic system of the target aircraft; the historical flight parameter data comprises state data of the hydraulic system of the target aircraft in a plurality of flight legs;
the first obtaining module is used for extracting the characteristics of the historical flight parameter data of the target aircraft hydraulic system to obtain the flight parameter characteristic data; the flight parameter characteristic data is used for representing the performance of the target aircraft hydraulic system;
a second obtaining module, configured to obtain, based on the flight parameter feature data, a composite distance model between the flight parameter feature data of any two flight frames of the target aircraft; the composite distance model is used for representing the difference between the same flight parameter characteristic data of any two flight frames of the target aircraft;
a third obtaining module, configured to obtain, based on the composite distance model, a correlation distance model of the flight parameter feature data between a certain flight frame of the target aircraft and the rest of the flight frames; the correlation distance model is used for evaluating the similarity of the same flight parameter characteristic data between a certain flight frame number and the rest flight frame numbers of the target aircraft;
and the identification module is used for identifying the abnormal frequency of the hydraulic system of the target aircraft based on the correlation distance model.
In a third aspect, the present application provides a computer device, which includes a memory and a processor, where the memory stores a computer program, and the processor executes the computer program to implement the method described in the embodiment.
In a fourth aspect, the present application provides a computer-readable storage medium having a computer program stored thereon, wherein a processor executes the computer program to implement the method described in the embodiments.
Through above-mentioned technical scheme, this application has following beneficial effect at least:
the method, the device, the equipment and the medium for identifying the performance abnormity of the aircraft hydraulic system are provided by the embodiment of the application, and the method comprises the steps of firstly obtaining historical flight parameter data of a target aircraft hydraulic system; the historical flight parameter data comprises state data of the hydraulic system of the target aircraft in a plurality of flight legs; then, extracting the characteristics of the historical flight parameter data of the target aircraft hydraulic system to obtain the flight parameter characteristic data; the flight parameter characteristic data is used for representing the performance of the hydraulic system of the target aircraft; then, based on the flight parameter characteristic data, obtaining a composite distance model between the flight parameter characteristic data of any two flight frames of the target aircraft; the composite distance model is used for representing the difference between the same flight parameter characteristic data of any two flight frames of the target aircraft; obtaining an associated distance model of the flight parameter characteristic data between a certain flight frame of the target aircraft and the rest flight frames based on the composite distance model; the correlation distance model is used for evaluating the similarity of the same flight parameter characteristic data between a certain flight frame number and the rest flight frame numbers of the target aircraft; and finally, identifying the abnormal frequency of the target aircraft hydraulic system based on the correlation distance model. Namely, when judging whether the hydraulic system of the target aircraft has abnormal conditions, historical flight parameter data of the hydraulic system of the target aircraft in the historical flight process are obtained, and then the historical flight parameter data are correspondingly processed to find out several key parameters, namely flight parameter characteristic data, which can influence the abnormal conditions of the hydraulic system most. And then selecting certain flight parameter characteristic data in a certain number of frames of the target aircraft to be sequentially compared with the same flight parameter characteristic data in other numbers of frames, and comparing every two numbers of frames to obtain the difference of the flight parameter characteristic data of the certain number of frames and the other numbers of frames, namely the composite distance. And then accumulating all the composite distances of a certain number of times compared with other numbers of times to obtain a measurement value of the number of times, namely the associated distance, and finally identifying whether the hydraulic system of the target aircraft is abnormal or not according to the associated distances. Namely, according to the method and the device, the same flight parameter characteristic data in the historical frequency of the target aircraft are correlated, and the same flight parameter characteristic data in the historical frequency are correlated, so that the variation trend of the same flight parameter characteristic data in the historical frequency of the target aircraft can be clearly known, and the flight parameter characteristic data can directly reflect the performance condition of the hydraulic system of the target aircraft, so that the performance degradation trend of the hydraulic system of the target aircraft can be more accurately judged, whether the hydraulic system of the target aircraft is abnormal or not can be more accurately identified, and the hydraulic system of the target aircraft can be more timely and more accurately maintained.
Drawings
FIG. 1 is a schematic diagram of a computer device in a hardware operating environment according to an embodiment of the present application;
FIG. 2 is a flowchart of a method for identifying performance anomalies of an aircraft hydraulic system according to an embodiment of the present disclosure;
fig. 3 is a schematic diagram of an aircraft hydraulic system performance abnormality recognition device according to an embodiment of the present application.
The implementation, functional features and advantages of the objectives of the present application will be further explained with reference to the accompanying drawings.
Detailed Description
It should be understood that the specific embodiments described herein are merely illustrative of and not restrictive on the broad application.
The airplane hydraulic system is used as an important energy transfer system to play an important role in driving movable parts on an airplane, the performance of the airplane hydraulic system is degraded and the use availability of the airplane is reduced when the airplane hydraulic system fails, major accidents are caused when the airplane hydraulic system fails, and the normal operation of the airplane hydraulic system is related to the safe use of the airplane. At present, the state detection and maintenance of an aircraft hydraulic system are generally carried out in a mode of combining flying parameter data analysis after flight with preventive maintenance, problems on the aircraft are found in time by carrying out manual interpretation on the flying parameter data so as to provide decision basis for flying in the next wave, maintenance work is carried out on the system on the aircraft through preventive maintenance (periodic work, regular inspection work and the like) so as to grasp the working state of the hydraulic system, and partial slight faults are prevented or serious faults are restrained from occurring. However, the flight parameter data of a single frame is only subjected to threshold range interpretation aiming at the physical quantity representing the working performance of the system, and the performance degradation trend of the flight parameter data cannot be judged; preventive maintenance is carried out by unconditionally stopping and timing according to a plan, routine inspection work is carried out more often, and the workload of the aircraft is increased without being discovered. In summary, at present, the performance degradation trend of the aircraft hydraulic system cannot be judged manually, so that whether the aircraft hydraulic system is abnormal or not cannot be identified accurately.
In order to solve the technical problems, the application provides a method, a device, equipment and a medium for identifying performance abnormality of an aircraft hydraulic system, and before a specific technical scheme of the application is introduced, a hardware operating environment related to the scheme of the embodiment of the application is introduced.
Referring to fig. 1, fig. 1 is a schematic structural diagram of a computer device in a hardware operating environment according to an embodiment of the present application.
As shown in fig. 1, the computer apparatus may include: a processor 1001, such as a Central Processing Unit (CPU), a communication bus 1002, a user interface 1003, a network interface 1004, and a memory 1005. Wherein a communication bus 1002 is used to enable connective communication between these components. The user interface 1003 may include a Display (Display), an input unit such as a Keyboard (Keyboard), and the optional user interface 1003 may also include a standard wired interface, a wireless interface. The network interface 1004 may optionally include a standard wired interface, a WIreless interface (e.g., a WIreless-FIdelity (WI-FI) interface). The Memory 1005 may be a Random Access Memory (RAM) Memory, or may be a Non-Volatile Memory (NVM), such as a disk Memory. The memory 1005 may alternatively be a storage device separate from the processor 1001.
Those skilled in the art will appreciate that the configuration shown in FIG. 1 does not constitute a limitation of a computer device and may include more or fewer components than those shown, or some components may be combined, or a different arrangement of components.
As shown in fig. 1, the memory 1005, which is a storage medium, may include therein an operating system, a data storage module, a network communication module, a user interface module, and an electronic program.
In the computer device shown in fig. 1, the network interface 1004 is mainly used for data communication with a network server; the user interface 1003 is mainly used for data interaction with a user; the processor 1001 and the memory 1005 in the computer device of the present invention may be disposed in the computer device, and the computer device calls the aircraft hydraulic system performance abnormality identification device stored in the memory 1005 through the processor 1001 and executes the aircraft hydraulic system performance abnormality identification method provided in the embodiment of the present application.
Referring to fig. 2, based on the hardware environment of the foregoing embodiment, an embodiment of the present application provides a method for identifying performance anomalies of an aircraft hydraulic system, where the method includes:
s10: acquiring historical flight parameter data of a target aircraft hydraulic system; the historical flight parameter data includes status data of the hydraulic system of the target aircraft over a number of flight legs.
In the specific implementation process, the target aircraft hydraulic system is the hydraulic system of the aircraft which needs to identify whether the hydraulic system has an abnormal condition, and the historical flight parameter data is the data of the target aircraft which can reflect the state of the target aircraft hydraulic system in the past. The historical flight parameter data of the target aircraft hydraulic system comprise hydraulic pressure, hydraulic oil temperature, a low hydraulic pressure alarm, a hydraulic pump power supply state and the like, the use state of the target aircraft hydraulic system can be directly reflected due to the hydraulic pressure, the hydraulic oil temperature, the low hydraulic pressure alarm, the hydraulic pump power supply state and the like, and the use state of the target aircraft hydraulic system can directly reflect the performance of the target aircraft hydraulic system. Therefore, the performance condition of the hydraulic system of the target aircraft can be identified by acquiring the data such as the hydraulic pressure, the hydraulic oil temperature, the low hydraulic pressure alarm, the power supply state of the hydraulic pump and the like. The historical flight parameter data of the target aircraft hydraulic system, such as hydraulic pressure, hydraulic oil temperature, low hydraulic pressure alarm, hydraulic pump power supply state and the like, are easy to obtain, and the obtaining cost is lower, namely the historical flight parameter data of the target aircraft hydraulic system can be obtained by conventional means. Therefore, whether the performance of the hydraulic system of the target aircraft is abnormal or not can be more easily identified after the historical flight parameter data are processed.
S11: extracting the characteristics of the historical flight parameter data of the target aircraft hydraulic system to obtain the flight parameter characteristic data; the flight parameter characteristic data is used for representing the performance of the hydraulic system of the target aircraft.
In a specific implementation process, the historical flight parameter data comprises flight parameter characteristic data, namely the flight parameter characteristic data is a parameter which is selected from the historical flight parameter data and can reflect the performance of a target aircraft hydraulic system. The historical flight parameter data comprise data which reflect the strong abnormal condition of the target aircraft hydraulic system and data which reflect the weak abnormal condition of the target aircraft hydraulic system, if the data are all processed and used for identifying the performance abnormality of the subsequent target aircraft hydraulic system, the amount of the historical flight parameter data is too large, and the cost for processing all the historical flight parameter data by a computer is higher and the efficiency is lower. Therefore, data which are relatively strong in reflecting the abnormal conditions of the target aircraft hydraulic system are extracted from the historical flight parameter data, so that the data processing amount of a computer can be greatly reduced, and the identification efficiency of the target aircraft hydraulic system can be greatly improved. Meanwhile, data which reflects the strong abnormal condition of the target aircraft hydraulic system, namely flight parameter characteristic data, is extracted, and the flight parameter characteristic data and the performance of the target aircraft hydraulic system belong to a strong correlation relationship, so that whether the abnormal condition exists in the target aircraft hydraulic system can be identified more accurately through the flight parameter characteristic data.
S12: acquiring a composite distance model between the flight parameter characteristic data of any two flight frames of the target aircraft based on the flight parameter characteristic data; the composite distance model is used for representing the difference between the same flight parameter characteristic data of any two flight frames of the target aircraft.
In the specific implementation process, after the flight parameter characteristic data are selected, a composite distance model which can represent any two flight parameters of the same target aircraft can be constructed through the flight parameter characteristic data. For example, the measured data of the same parameter of the same target aircraft are n and m on two different flight frames, and n and m may be the same or different. When n and m are different, the flight parameter characteristic data representing the two flight frames are different, namely the flight parameter characteristic data is changed, the performance change condition of the target aircraft hydraulic system can be reflected by the change amount and the difference size (namely the composite distance between the flight parameter characteristic data) of the flight parameter characteristic data in the two flight frames, and whether the target aircraft hydraulic system has an abnormal condition or not can be known according to the performance change condition of the target aircraft hydraulic system. Therefore, the difference, namely the difference, of a certain flight parameter characteristic of the target aircraft in two different flight frames can be embodied through the composite distance model, and the performance change condition of the hydraulic system of the target aircraft can be embodied. Specifically, a composite distance model between the flight parameter characteristic data of any two flight frames of the target aircraft is obtained through the following relational expression:
r(i，j)＝d(q i ，c j )+min{r(i-1，j-1)，r(i-1，j)，r(i，j-1)}
wherein r (i, j) represents a composite distance model between the ith and jth shelves of the target aircraft，d(q i ，c j ) Representing q on the ith rack of the target aircraft i Point and c on the jth frame j And (4) expressing the minimum value of Euclidean distance between points, wherein min { } represents the selected minimum value.
S13: based on the composite distance model, obtaining an associated distance model of the flight parameter characteristic data between a certain flight frame of the target aircraft and the rest flight frames; and the association distance model is used for evaluating the similarity of the same flight parameter characteristic data between a certain flight frame of the target aircraft and the rest flight frames.
In the specific implementation process, firstly, comparing each frame of data between two shelves of the target aircraft, and calculating a result to measure the shelves (dimensionless); and then, comparing the data of all the frames pairwise, for example, comparing the A, B, C and D frames, respectively, obtaining four results (namely four composite distances) after comparison, and adding the four results to be used as the measurement value of the A frame. According to the same method, measurement values (associated distances) of the B-frame number, the C-frame number and the D-frame number can be obtained, finally, standard deviations sigma of the measurement values of the A-frame number, the B-frame number, the C-frame number and the D-frame number are obtained, and then the abnormal condition of the target hydraulic system is judged based on the standard deviations sigma. For example, the abnormality is determined based on the 3-fold standard deviation σ, that is, if the measurement value (associated distance) of a certain frame is greater than the 3-fold standard deviation σ, it is determined that the hydraulic system corresponding to the frame exists. Therefore, the flight parameter characteristic data of the target aircraft can be correlated, and whether the hydraulic system of the target aircraft has abnormal conditions or not can be accurately identified. When the flight parameter characteristic data and the number of the shelves of the target aircraft are more, the future number of the shelves of the target aircraft can be predicted, and therefore relevant personnel can maintain the target aircraft identified with the abnormality in advance, and the safety of the corresponding number of the shelves of the target aircraft can be improved. Specifically, a correlation distance model of the flight parameter feature data between a certain flight frame of the target aircraft and the rest of the flight frames is obtained through the following relational expression:
the cost represents an associated distance model of flight parameter characteristic data between a certain flight frame number and the rest flight frame numbers of the target aircraft, and N represents the total number of the historical flight frame numbers of the target aircraft.
More specifically, a dynamic time warping algorithm (DTW) is used to calculate a composite distance r (i, j) between any two sets of flight parameter data, where r (i, j) is a distance d (i, j) of a frame of data, that is, the sum of the euclidean distance between two points qi and cj on the two sets of flight parameter data and the composite distance of the minimum adjacent element that can reach the point, from represents a starting point, to represents an end point, and cost is a distance from the from set to the to set (assuming that N sets are available), and a cost value is used to evaluate the similarity between the from set and all to sets, so as to represent the centroid of the set.
S14: and identifying the abnormal frequency of the target aircraft hydraulic system based on the correlation distance model.
In the specific implementation process, the flight parameter characteristic data of the target aircraft can be correlated through the correlation distance model, and the abnormal condition of the hydraulic system of the target aircraft is judged through the comparison of the flight parameter characteristic data.
In summary, when it is determined whether the hydraulic system of the target aircraft has an abnormal condition, the historical flight parameter data of the hydraulic system of the target aircraft in the historical flight process is obtained first, and then the historical flight parameter data is processed correspondingly to find out several key parameters, namely flight parameter characteristic data, which can most affect whether the hydraulic system has the abnormal condition. And then selecting certain flight parameter characteristic data in a certain number of frames of the target aircraft to be sequentially compared with the same flight parameter characteristic data in other numbers of frames, and comparing every two numbers of frames to obtain the difference of the flight parameter characteristic data of the certain number of frames and the other numbers of frames, namely the composite distance. And then accumulating all the composite distances of a certain number of times compared with other numbers of times to obtain a measurement value of the number of times, namely the associated distance, and finally identifying whether the hydraulic system of the target aircraft is abnormal or not according to the associated distances. Namely, according to the method and the device, the same flight parameter characteristic data in the historical number of the target aircraft are correlated, and the same flight parameter characteristic data in the historical number of the target aircraft are correlated, so that the change trend of the same flight parameter characteristic data in the historical number of the target aircraft can be clearly known, and the flight parameter characteristic data can directly reflect the performance condition of the hydraulic system of the target aircraft, so that the performance decline trend of the hydraulic system of the target aircraft can be more accurately judged, whether the hydraulic system of the target aircraft is abnormal or not can be more accurately identified, and the hydraulic system of the target aircraft can be more timely and more accurately maintained.
In order to better utilize the correlation distance model to identify whether the hydraulic system of the target aircraft has an abnormality, an optional technical scheme is provided in some embodiments as follows: the step of identifying the abnormal frequency of the target aircraft hydraulic system based on the correlation distance model comprises the following steps:
firstly, based on the correlation distance model, obtaining a standard deviation of correlation distances among the flight parameter feature data of the target aircraft for a plurality of times; and then identifying the abnormal number of the target aircraft hydraulic system based on the standard deviation. Specifically, an abnormality judgment threshold is preset based on the standard deviation; the preset abnormal judgment threshold comprises H times of standard deviation; wherein H is a positive number; and then identifying the abnormal frequency of the hydraulic system of the target aircraft based on the abnormal judgment threshold value.
In this embodiment, that is, a determination model capable of determining whether the flight parameter feature data of the target aircraft is abnormal is preset, then a standard deviation of the association distances of all the flight parameter feature data is obtained, then the obtained standard deviation is compared with a determination threshold, if the association distance corresponding to a certain number of flying frames of the target aircraft is greater than an abnormality determination threshold, the flight parameter feature data is determined to be abnormal data, and since the flight parameter feature data can directly reflect whether the corresponding number of flying frames is abnormal, it can be determined that the number of flying frames is an abnormal number. More specifically, the value of H is preferably 3, the cost value calculated according to the historical flight parameter data is used for calculating the mean value μ and the standard deviation σ of the current sample, the historical data abnormal point criterion is set according to the confidence coefficient of 99.7%, and the corresponding abnormal frame number exceeding the range of 3 σ is identified.
In order to better utilize the result of the determination, in some embodiments, a preferable scheme is provided, that if the associated distance corresponding to a certain number of flights of the target aircraft is greater than the abnormality determination threshold, the step of determining that the certain number of flights is an abnormal number further includes: checking whether a hydraulic system of the target aircraft corresponding to the abnormal frame number is normal or not; if the hydraulic system of the target aircraft is abnormal, setting a treatment suggestion instruction; wherein the treatment recommendation command comprises a command to change a hydraulic system of the target aircraft from abnormal to normal; if the hydraulic system of the target aircraft is normal, setting a reset instruction; wherein the reset instruction comprises an instruction to adjust the anomaly determination threshold.
In this embodiment, the result of data anomaly identification may be analyzed and determined manually, and if the result of data anomaly is true, a corresponding disposal recommendation instruction is added to the result of data anomaly identification, and the anomaly point criterion is used; and if the abnormal result is false, adjusting the H-time standard deviation of the judgment threshold according to the result confidence, and calculating again until the judgment result is correct.
In order to better obtain the flight parameter feature data, in some embodiments, the step of performing feature extraction on the historical flight parameter data of the target aircraft hydraulic system to obtain the flight parameter feature data comprises: firstly, storing historical flight parameter data of the target aircraft hydraulic system; then classifying the stored historical flight parameter data according to different data types; then respectively extracting feature matrixes of the classified historical flight parameter data; and finally, carrying out normalization processing on the feature matrix of the historical flight parameter data to obtain the flight parameter feature data.
In this embodiment, after data processing is performed on historical flight parameter data, system parameter configuration is called to generate engineering value data of a corresponding system, the engineering value data stores a distributed file system, and flight parameter data file information and data configuration information are stored in a Mysql relational database. The data feature extraction module acquires engineering value data and flight state data of the system, divides different flight stages in a flight frame according to flight stage division criteria, respectively extracts data features of respective stages after dimension reduction according to continuous quantity and discrete quantity data types, and determines key flight parameter parameters by adopting a principal component analysis method. Firstly, researching the composition of flight parameter original data and the information content of flight parameter data parameters, respectively storing semi-structured data such as data files by using an HDFS distributed storage platform, storing structured data such as flight parameter data parameter information by using a relational database Mysql, and storing acquired historical flight parameter data; respectively extracting characteristic matrixes from the stored historical flying parameter data of the hydraulic system according to different data types, carrying out normalization processing on the characteristic matrixes, calculating characteristic values and characteristic vectors of covariance matrixes, multiplying the characteristic vectors by the covariance matrixes to obtain scoring characteristic matrixes, and determining key flying parameter data, namely the flying parameter characteristic data.
To further facilitate identifying whether an anomaly exists in the target aircraft hydraulic system, in some embodiments, the step of identifying the number of times the target aircraft hydraulic system is anomalous based on the correlation distance model comprises: firstly, obtaining a variation trend graph of the correlation distance of the target aircraft flying frame based on the correlation distance model; and then identifying the abnormal number of the target aircraft hydraulic system based on the change trend graph of the associated distance of the target aircraft flight number.
In the embodiment, historical flight parameter data are plotted according to a time sequence, the abscissa of the plotted graph represents the number of flight parameter frames/time, the ordinate represents the cost value, and the judgment threshold value parallel to the abscissa is detected and plotted in the graph, so that the abnormal conditions of the hydraulic system of which frames of the target aircraft occur can be judged more visually through the plotted graph, the efficiency of judging the abnormal conditions of the hydraulic system of the target aircraft can be improved, possible faults of the hydraulic system can be found earlier, and a decision basis is provided for maintenance according to the conditions.
In conclusion, the method comprehensively analyzes the historical flight parameter data, firstly carries out dimension reduction identification on the flight parameter key parameters, secondly introduces a dynamic time warping algorithm to carry out centroid fitting on the past flight parameter data, and finally combines the historical data abnormal point criterion to carry out abnormal identification on the past flight parameter data fitting curve, establishes a system analysis process, provides decision basis for the condition-based maintenance without additionally increasing the workload, and has good popularization value. The method is characterized in that a data feature extraction module, a historical data association module and a trend abnormity judgment module are set up, extraction generation and centroid fitting of the flight parameter data of the hydraulic system are completed, abnormal trends of the historical flight parameter data are identified, possible faults are found as soon as possible, and a decision basis is provided for on-the-fly maintenance. In a word, the application provides an aircraft hydraulic system performance abnormity identification method based on dynamic time warping, the performance decline trend of a hydraulic system is monitored under the condition of lacking of a fault mechanism, flying parameter data processing, distributed file storage, feature extraction and performance abnormity judgment operations are effectively completed, data batch processing, data feature extraction, flying parameter data principal component analysis and abnormity identification module generation are realized, and the problem that an aircraft is difficult to acquire fault hidden danger is solved.
In another embodiment, as shown in fig. 3, based on the same inventive concept as the previous embodiment, an embodiment of the present application further provides an engine thrust pin quick dismounting device, including:
the acquisition module is used for acquiring historical flight parameter data of a hydraulic system of a target aircraft; the historical flight parameter data comprises state data of the hydraulic system of the target aircraft in a plurality of flight frames;
the first obtaining module is used for extracting the characteristics of the historical flight parameter data of the target aircraft hydraulic system to obtain flight parameter characteristic data; the flight parameter characteristic data is used for representing the performance of the target aircraft hydraulic system;
the second obtaining module is used for obtaining a composite distance model between the flight parameter characteristic data of any two flight frames of the target aircraft based on the flight parameter characteristic data; the composite distance model is used for representing the difference between the same flight parameter characteristic data of any two flight frames of the target aircraft;
a third obtaining module, configured to obtain, based on the composite distance model, a correlation distance model of the flight parameter feature data between a certain flight frame of the target aircraft and the rest of the flight frames; the correlation distance model is used for evaluating the similarity of the same flight parameter characteristic data between a certain flight frame number and the rest flight frame numbers of the target aircraft;
and the identification module is used for identifying the abnormal frequency of the target aircraft hydraulic system based on the correlation distance model.
It should be noted that, in this embodiment, each module in the device for identifying performance abnormality of an aircraft hydraulic system corresponds to each step in the method for identifying performance abnormality of an aircraft hydraulic system in the foregoing embodiment one by one, and therefore, the specific implementation and achieved technical effect of this embodiment may refer to the implementation of the method for identifying performance abnormality of an aircraft hydraulic system, and are not described herein again.
Furthermore, in an embodiment, the present application also provides a computer device, which includes a processor, a memory and a computer program stored in the memory, and when the computer program is executed by the processor, the method in the foregoing embodiment is implemented.
Furthermore, in an embodiment, the present application further provides a computer storage medium, on which a computer program is stored, and the computer program is executed by a processor to implement the method in the foregoing embodiment.
In some embodiments, the computer-readable storage medium may be memory such as FRAM, ROM, PROM, EPROM, EEPROM, flash, magnetic surface memory, optical disk, or CD-ROM; or may be various devices including one or any combination of the above memories. The computer may be a variety of computing devices including intelligent terminals and servers.
In some embodiments, executable instructions may be written in any form of programming language (including compiled or interpreted languages), in the form of programs, software modules, scripts or code, and may be deployed in any form, including as a stand-alone program or as a module, component, subroutine, or other unit suitable for use in a computing environment.
By way of example, executable instructions may correspond, but do not necessarily have to correspond, to files in a file system, and may be stored in a portion of a file that holds other programs or data, such as in one or more scripts in a hypertext Markup Language (HTML) document, in a single file dedicated to the program in question, or in multiple coordinated files (e.g., files that store one or more modules, sub-programs, or portions of code).
By way of example, executable instructions may be deployed to be executed on one computing device or on multiple computing devices at one site or distributed across multiple sites and interconnected by a communication network.
It should be noted that, in this document, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or system that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or system. Without further limitation, an element defined by the phrases "comprising a," "8230," "8230," or "comprising" does not exclude the presence of other like elements in a process, method, article, or system comprising the element.
The above-mentioned serial numbers of the embodiments of the present application are merely for description and do not represent the merits of the embodiments.
Through the above description of the embodiments, those skilled in the art will clearly understand that the method of the above embodiments can be implemented by software plus a necessary general hardware platform, and certainly can also be implemented by hardware, but in many cases, the former is a better implementation manner. Based on such understanding, the technical solutions of the present application may be embodied in the form of a software product, which is stored in a storage medium (e.g., a rom/ram, a magnetic disk, an optical disk) and includes instructions for enabling a multimedia terminal (e.g., a mobile phone, a computer, a television receiver, or a network device) to execute the method according to the embodiments of the present application.
The above description is only a preferred embodiment of the present application, and not intended to limit the scope of the present application, and all the equivalent structures or equivalent processes that can be directly or indirectly applied to other related technical fields by using the contents of the specification and the drawings of the present application are also included in the scope of the present application.
Claims (11)
1. An aircraft hydraulic system performance anomaly identification method is characterized by comprising the following steps:
acquiring historical flight parameter data of a target aircraft hydraulic system; the historical flight parameter data comprises state data of the hydraulic system of the target aircraft in a plurality of flight legs;
extracting the characteristics of the historical flight parameter data of the target aircraft hydraulic system to obtain the flight parameter characteristic data; the flight parameter characteristic data is used for representing the performance of the target aircraft hydraulic system;
acquiring a composite distance model between the flight parameter characteristic data of any two flight frames of the target aircraft based on the flight parameter characteristic data; the composite distance model is used for representing the difference between the same flight parameter characteristic data of any two flight frames of the target aircraft;
based on the composite distance model, obtaining an associated distance model of the flight parameter characteristic data between a certain flight frame and the rest flight frames of the target aircraft; the correlation distance model is used for evaluating the similarity of the same flight parameter characteristic data between a certain flight frame number and the rest flight frame numbers of the target aircraft;
and identifying the abnormal number of the target aircraft hydraulic system based on the correlation distance model.
2. The method for identifying an aircraft hydraulic system performance anomaly according to claim 1, wherein the identifying the rack of the target aircraft hydraulic system anomaly based on the correlation distance model comprises:
based on the correlation distance model, obtaining a standard deviation of correlation distances among the flight parameter feature data of a plurality of times of the target aircraft;
and identifying the abnormal frequency of the target aircraft hydraulic system based on the standard deviation.
3. The method for identifying performance anomalies of an aircraft hydraulic system according to claim 2, wherein the identifying the number of occurrences of the target aircraft hydraulic system anomalies based on the standard deviation includes:
presetting an abnormal judgment threshold value based on the standard deviation; the preset abnormal judgment threshold comprises H times of standard deviation; wherein H is a positive number;
and identifying the abnormal frequency of the target aircraft hydraulic system based on the abnormal judgment threshold value.
4. The method for identifying performance anomalies of aircraft hydraulic systems according to claim 3, wherein identifying the number of times the target aircraft hydraulic system is anomalous based on the anomaly determination threshold comprises:
and if the associated distance corresponding to a certain flight number of the target aircraft is greater than the abnormal judgment threshold value, judging that the flight number is an abnormal number.
5. The method for identifying performance abnormality of an aircraft hydraulic system according to claim 4, wherein after the step of determining that a certain flying rack of the target aircraft corresponds to the correlation distance greater than the abnormality determination threshold, the method further comprises:
checking whether a hydraulic system of the target aircraft corresponding to the abnormal number of the stands is normal or not;
if the hydraulic system of the target aircraft is abnormal, setting a disposal suggestion instruction; wherein the treatment recommendation command comprises a command to change a hydraulic system of the target aircraft from abnormal to normal;
if the hydraulic system of the target aircraft is normal, setting a reset instruction; wherein the reset instruction comprises an instruction to adjust the anomaly determination threshold.
6. An aircraft hydraulic system performance anomaly identification method according to any one of claims 1-5, wherein the identifying the number of anomalies of the target aircraft hydraulic system based on the correlation distance model comprises:
obtaining a variation trend graph of the correlation distance of the target aircraft flying frame number based on the correlation distance model;
and identifying the abnormal number of the target aircraft hydraulic system based on the change trend graph of the associated distance of the target aircraft flight number.
7. The method for identifying performance anomalies of an aircraft hydraulic system according to claim 1, wherein the step of performing feature extraction on the historical flight parameter data of the target aircraft hydraulic system to obtain flight parameter feature data comprises the following steps:
storing historical flight parameter data of the target aircraft hydraulic system;
classifying the stored historical flight parameter data according to different data types;
respectively extracting feature matrixes of the classified historical flight parameter data;
and carrying out normalization processing on the feature matrix of the historical flight parameter data to obtain the flight parameter feature data.
8. The method for identifying performance anomalies of an aircraft hydraulic system according to claim 1, wherein the obtaining a composite distance model between the flight parameter feature data of any two flight legs of the target aircraft based on the flight parameter feature data includes:
obtaining a composite distance model between the flight parameter characteristic data of any two flight times of the target aircraft through the following relational expression:
r(i,j)＝d(q i ,c j )+min{r(i-1,j-1),r(i-1,j),r(i,j-1)}
wherein r (i, j) represents the target aircraftModel of the composite distance between the i-th and j-th frames, d (q) i ,c j ) Representing q on the ith rack of the target aircraft i Point and c on the jth frame j The Euclidean distance between points, min { } represents the minimum value selected;
the obtaining of the associated distance model of the flight parameter feature data between a certain flight frame and the rest flight frames of the target aircraft based on the composite distance model comprises:
obtaining an association distance model of the flight parameter characteristic data between a certain flight frame of the target aircraft and the rest flight frames through the following relational expression:
the cost represents an associated distance model of flight parameter characteristic data between a certain flight frame number and the rest flight frame numbers of the target aircraft, and N represents the total number of the historical flight frame numbers of the target aircraft.
9. An aircraft hydraulic system performance anomaly identification device, the device comprising:
the acquisition module is used for acquiring historical flight parameter data of a hydraulic system of a target aircraft; the historical flight parameter data comprises state data of the hydraulic system of the target aircraft in a plurality of flight frames;
the first obtaining module is used for extracting the characteristics of the historical flight parameter data of the target aircraft hydraulic system to obtain the flight parameter characteristic data; the flight parameter characteristic data is used for representing the performance of the target aircraft hydraulic system;
a second obtaining module, configured to obtain, based on the flight parameter feature data, a composite distance model between the flight parameter feature data of any two flight frames of the target aircraft; the composite distance model is used for representing the difference between the same flight parameter characteristic data of any two flight frames of the target aircraft;
a third obtaining module, configured to obtain, based on the composite distance model, a correlation distance model of the flight parameter feature data between a certain flight frame of the target aircraft and the rest of the flight frames; the correlation distance model is used for evaluating the similarity of the same flight parameter characteristic data between a certain flight frame number and the rest flight frame numbers of the target aircraft;
and the identification module is used for identifying the abnormal frequency of the target aircraft hydraulic system based on the correlation distance model.
10. A computer arrangement, characterized in that the computer arrangement comprises a memory in which a computer program is stored and a processor which executes the computer program for implementing the method as claimed in any one of claims 1-8.
11. A computer-readable storage medium, having a computer program stored thereon, which, when executed by a processor, performs the method of any one of claims 1-8.
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