Knowledge graph construction method and system for airplane electromechanical product parameter traceability

Abstract

The invention belongs to the technical field of aviation digital measurement, and discloses a knowledge graph construction method and system for aircraft electromechanical product parameter traceability, and the method comprises the steps: obtaining the data of an aircraft electromechanical product parameter traceability form; based on the airplane electromechanical product parameter traceability form data, obtaining airplane electromechanical product parameter traceability graphic data; and complementing the airplane electromechanical product parameter traceability graphic data. According to the method, the aviation parameter traceability chain is constructed based on the graph database constructed by the knowledge graph, so that a conventional design-test-metering separated quantity value traceability mode adopted by an airplane electromechanical product at present is replaced, and the problem that a metering means for parameter traceability by using a paper document at present is seriously deficient is solved; and the measuring level of airplane electromechanical products is effectively improved.

Description

Technical Field

[0001] The present invention relates to the field of aviation digital metrology technology, and more specifically, to a knowledge graph construction method and system for aircraft electromechanical product parameter traceability. Background Art

[0002] As an important technical foundation, metrology is an activity to achieve unit unification and ensure the accuracy and reliability of measurement values. Measurement traceability and measurement transfer are the main ways to achieve measurement unification. High-quality completion of measurement traceability of various products of aircraft systems plays an important basic supporting role in ensuring product quality and reliable performance in the aircraft industry. With the continuous development of my country's aircraft industry, aircraft must meet airworthiness management requirements. It is necessary to use mature metrology methods to verify the accuracy of data provided by products from development to operation to ensure the safety of aircraft performance. For this reason, the demand for measurement traceability is increasing and the requirements are getting higher and higher. At present, the metrology assurance system established by domestic aircraft manufacturing enterprises mostly only focuses on the level of measuring equipment and ignores the control of the measurement process. Most of the metrology work is still the laboratory verification / calibration activities of measuring instruments, which is difficult to meet the technical requirements of measurement assurance in the aircraft development process and support product airworthiness compliance verification. Summary of the invention

[0003] The purpose of the present invention is to provide a knowledge graph construction method and system for aircraft electromechanical product parameter traceability, so as to propose a new digital metrology solution that can establish a traceability chain of "aircraft product parameters-test equipment parameters-calibration equipment (including working metrological instruments) parameters" from the perspective of strengthening measurement process control and improving the metrology assurance system.

[0004] In order to achieve the above object, the present invention adopts the following technical solution:

[0005] According to a first aspect of the present invention, a method for constructing a knowledge graph for aircraft electromechanical product parameter traceability is provided, the method comprising:

[0006] Obtain aircraft electromechanical product parameter traceability form data;

[0007] Based on the aircraft electromechanical product parameter traceability form data, obtaining aircraft electromechanical product parameter traceability graphic data;

[0008] The aircraft electromechanical product parameter traceability graphic data is completed.

[0009] According to a second aspect of the present invention, a knowledge graph construction system for aircraft electromechanical product parameter traceability is provided, the system comprising:

[0010] A form data acquisition module, configured to acquire aircraft electromechanical product parameter traceability form data;

[0011] A graphic data acquisition module, configured to acquire aircraft electromechanical product parameter traceability graphic data based on the aircraft electromechanical product parameter traceability form data;

[0012] The graphic data completion module is configured to complete the aircraft electromechanical product parameter traceability graphic data.

[0013] The present invention has at least the following beneficial effects:

[0014] The present invention completes the construction of the aviation parameter traceability chain based on a graphic database constructed based on a knowledge graph, so as to replace the traditional value traceability method of design-test-measurement separation currently used in aircraft electromechanical products, improve the serious lack of metrological means for parameter traceability based on paper documents, and effectively improve the metrology level of aircraft electromechanical products. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 A flowchart of a method for constructing a knowledge graph for aircraft electromechanical product parameter traceability according to an embodiment of the present invention is shown.

[0016] Figure 2 A schematic diagram of a traceability chain of metrological parameters—testing equipment—calibration equipment according to an embodiment of the present invention is shown.

[0017] Figure 3 A power prediction line graph according to an embodiment of the present invention is shown.

[0018] Figure 4 A structural diagram of a knowledge graph construction system for aircraft electromechanical product parameter traceability according to an embodiment of the present invention is shown. DETAILED DESCRIPTION

[0019] In order to enable those skilled in the art to better understand the technical solution of the present invention, the present invention is described in detail below in conjunction with the accompanying drawings and specific embodiments. The embodiments of the present invention are further described in detail below in conjunction with the accompanying drawings and specific embodiments, but are not intended to limit the present invention. For the various steps described herein, if there is no necessity for a causal relationship between each other, the order in which they are described as examples herein should not be regarded as a limitation, and those skilled in the art should know that they can be adjusted in order, as long as the logic between them is not destroyed, resulting in the inability to implement the entire process.

[0020] The embodiment of the present invention provides a knowledge graph construction method for aircraft electromechanical product parameter traceability. Figure 1 The method includes steps S1 to S3, which are described in detail as follows:

[0021] S1. Obtain the aircraft electromechanical product parameter traceability form data.

[0022] In this embodiment, the aircraft electromechanical product parameter traceability form data may be in the form of an Excel form. In one embodiment, the aircraft electromechanical product parameter traceability form database obtained in step S1 includes 7 Excel forms, and the form names are respectively set to: aircraft system, aircraft component, measurement unit, measurement parameter, special detection equipment, general detection equipment and calibration equipment.

[0023] Specifically, the data in each column of the 7 Excel sheets from left to right are set as follows:

[0024] 1) Aircraft system table (4 columns, as shown in Table 1):

[0025] Aircraft name, T0 system, T1 subsystem, T2 subsystem.

[0026] Table 1 Aircraft systems

[0027] Aircraft Name T0 System T1 subsystem T2 Subsystem XXX Aircraft Aircraft body XXX Aircraft Power plant (engine) XXX Aircraft Airborne Systems Avionics System Communication System XXX Aircraft Airborne Systems Avionics System Information Systems

[0028] 2) Aircraft parts (12 columns, as shown in Table 2):

[0029] T3 components, T3 models, T3 supplier name, T3 factory number, T3 environmental requirements, T3 test basis technical documents, T3 notes, T3 attachments, T2 subsystem name, T1 subsystem name, T0 system name, aircraft name.

[0030] Table 2 Aircraft parts

[0031]

[0032]

[0033] 3) Units of measurement (8 columns, as shown in Table 3):

[0034] Category Name, Unit 1, 1To2, Unit 2, 2To3, Unit 3, 3To4, Unit 4.

[0035] Table 3 Units of measurement

[0036] Category Name Unit 1 1To2 Unit 2 2To3 Unit 3 3To4 Unit 4 Force N 1000 kN 1000 MN pressure Pa 1000 kPa 1000 MPa frequency Hz 1000 kHz 1000 MHz

[0037] 4) Metering parameters (18 columns, as shown in Table 4):

[0038] T3 name, T2 name, T1 name, T0 name, aircraft name, DP name, DP use range or value, DP use allowable error, DP use lower limit, DP use upper limit, DP tolerance lower limit, DP tolerance upper limit, DP tolerance percentage lower limit, DP tolerance percentage upper limit, DP value, DP measurement conditions, whether DP is specially tested, unit 1.

[0039] Table 4 Measurement parameters

[0040]

[0041]

[0042] 5) Special testing equipment (20 columns, as shown in Table 5):

[0043] SDP name, SDP detection components, SDP measurement parameters, SDS name, SDS model, SDS manufacturer, SDS measurement range, SDS maximum allowable error or accuracy level, SDS remarks, SDS measurement lower limit, SDS measurement upper limit, SDS tolerance percentage lower limit, SDS tolerance percentage upper limit, SDS tolerance lower limit, SDS tolerance upper limit, SDSFS, SDS accuracy level, SDS validity period, SDS measurement conditions, unit 1.

[0044] Table 5 Special testing equipment

[0045]

[0046] 6) General testing equipment (19 columns, as shown in Table 6):

[0047] GD name, GD model, GD manufacturer, GD components, GD measurement parameters, GD measurement range, GD maximum allowable error or accuracy grade, GD remarks, GD measurement lower limit, GD measurement upper limit, GD tolerance percentage lower limit, GD tolerance percentage upper limit, GD tolerance lower limit, GD tolerance upper limit, GDFS, GD accuracy grade, GD validity period, GD measurement conditions, unit 1.

[0048] Table 6 General testing equipment

[0049]

[0050] 7) Calibration equipment (20 columns, as shown in Table 7):

[0051] Ca name, Ca model, Ca calibration basis technical documents, Ca components, Ca measurement parameters, Ca remarks, Ca measurement range, Ca maximum allowable error or accuracy grade, Ca measurement lower limit, Ca measurement upper limit, Ca tolerance percentage lower limit, Ca tolerance percentage upper limit, Ca tolerance lower limit, Ca tolerance upper limit, CaFS, Ca accuracy grade, Ca measurement uncertainty, Ca validity period, Ca measurement conditions, unit 1.

[0052] Table 7 Calibration equipment

[0053]

[0054] S2. Based on the aircraft electromechanical product parameter traceability form data, obtain aircraft electromechanical product parameter traceability graphic data.

[0055] In some embodiments, the aircraft electromechanical product parameter traceability graphic data obtained in step S2 is constructed by importing the seven Excel sheets in step S1 into the Neo4J graphic database; wherein, the data in the column of "unit 1" in the measurement parameters, special testing equipment, general testing equipment and calibration equipment sheets are not imported into the graphic database, but are associated with the "measurement unit" sheet in step S1; the image data is presented in the form of "node-edge-node", such as Figure 2 As shown, the node name is set to the leftmost column of the form data in step S1, and the edges are set in the following form: 1) Aircraft system: aircraft name - includes - aircraft parts: T2 name; 2) Aircraft parts: T2 name - includes - measurement parameters: T3 name; 3) Measurement parameters: T3 name - includes - measurement units: category name; 4) Special testing equipment: SDP name - detection - measurement parameters: T3 name; 5) General testing equipment: GD name - detection - measurement parameters: T3 name; 6) Calibration equipment: Ca name - calibration - general testing equipment: GD name; 7) Calibration equipment: Ca name - calibration - special testing equipment: SDP name.

[0056] In some embodiments, the graphic data edges of "special testing equipment: SDP name - testing - measurement parameters: T3 name", "general testing equipment: GD name - testing - measurement parameters: T3 name", "calibration equipment: Ca name - calibration - general testing equipment: GD name", and "calibration equipment: Ca name - calibration - special testing equipment: SDP name" are associated in the following manner:

[0057] 1) Special testing equipment - testing - measurement parameters:

[0058] If the SDP detection component in the dedicated detection device form is consistent with the T3 name in the metering parameter form and the SDP measurement parameter in the dedicated detection device form is consistent with the DP name in the metering parameter form, construct an edge between the dedicated detection device SDP name and the T3 name in the metering parameter form in the graph database;

[0059] 2) General testing equipment - testing - measurement parameters:

[0060] If the GD component in the general test equipment form is consistent with the T3 name in the metrology parameter form and the GD measurement parameter in the general test equipment form is consistent with the DP name in the metrology parameter form, then an edge between the general test equipment GD name and the T3 name in the metrology parameter form is constructed in the graph database;

[0061] 3) Calibration equipment - Calibration - General testing equipment:

[0062] If the Ca component in the calibration equipment form is consistent with the GD component in the general test equipment form and the Ca measurement parameter in the calibration equipment form is consistent with the GD name in the special test equipment form, then an edge between the calibration equipment Ca name and the GD name in the general test equipment form is constructed in the graph database;

[0063] 4) Calibration equipment - Calibration - Special testing equipment:

[0064] If the Ca component in the calibration equipment form is consistent with the SDP component in the dedicated detection equipment form and the Ca measurement parameter in the calibration equipment form is consistent with the SDP name in the dedicated detection equipment form, then an edge between the calibration equipment Ca name and the SDP name in the dedicated detection equipment form is constructed in the graph database.

[0065] S3. Complete the traceability graphic data of aircraft electromechanical product parameters.

[0066] In some embodiments, the aircraft electromechanical product parameter traceability graphic data completion in step S3 is divided into the following four situations:

[0067] Case 1: For general testing equipment - testing - measurement parameters:

[0068] If the metrology parameter is missing for the universal test equipment, proceed as follows:

[0069] S311. Searching for the GD name of the general testing equipment whose "unit 1" is consistent with the measurement parameter "unit 1" in the general testing equipment form;

[0070] S312. Filter out the general testing equipment GD names that simultaneously meet the following conditions: general testing equipment GD measurement range > metrological parameter DP usage range or value, GD maximum allowable error < (1 / 3 metrological parameter DP usage allowable error), GD measurement lower limit < DP usage lower limit, GD measurement upper limit > DP usage upper limit, GD tolerance percentage lower limit < DP tolerance percentage lower limit, GD tolerance percentage upper limit > DP tolerance percentage upper limit, GD tolerance lower limit < DP tolerance lower limit, GD tolerance upper limit greater than DP tolerance upper limit, and construct an edge between the general testing equipment GD name and the T3 name in the metrological parameter form.

[0071] Case 2: For dedicated testing equipment - testing - measurement parameters:

[0072] If the measurement parameters are missing a dedicated test device, follow the steps below:

[0073] S321. Retrieve the SDP name of the special testing equipment whose "unit 1" is consistent with the measurement parameter "unit 1" in the special testing equipment form;

[0074] S322. Filter out the special testing equipment SDP names that simultaneously meet the following conditions: special testing equipment SDS measurement range > metrological parameter DP usage range or value, SDS maximum allowable error < (1 / 3 metrological parameter DP usage allowable error), SDS measurement lower limit < DP usage lower limit, SDS measurement upper limit > DP usage upper limit, SDS tolerance percentage lower limit < DP tolerance percentage lower limit, SDS tolerance percentage upper limit > DP tolerance percentage upper limit, SDS tolerance lower limit < DP tolerance lower limit, SDS tolerance upper limit greater than DP tolerance upper limit, and construct an edge between the special testing equipment SDP name and the T3 name in the metrological parameter form.

[0075] Case 3: For calibration equipment - calibration - general testing equipment:

[0076] If the universal test equipment is missing the calibration equipment, such as Figure 3 As shown, follow these steps:

[0077] S331, searching the calibration equipment table for the calibration equipment Ca name whose "unit 1" is consistent with the general testing equipment "unit 1";

[0078] S332. Filter out the calibration equipment Ca names that simultaneously meet the following conditions: calibration equipment Ca measurement range > general calibration equipment GD use range or value, Ca maximum allowable error < (1 / 3GD use allowable error), Ca measurement lower limit < GD use lower limit, Ca measurement upper limit > GD use upper limit, Ca tolerance percentage lower limit < GD tolerance percentage lower limit, Ca tolerance percentage upper limit > GD tolerance percentage upper limit, Ca tolerance lower limit < GD tolerance lower limit, Ca tolerance upper limit > GD tolerance upper limit, and construct an edge between the calibration equipment Ca name and the GD name in the general testing equipment form.

[0079] Case 4: For calibration equipment - calibration - dedicated test equipment:

[0080] If the dedicated test equipment is missing the calibration equipment, follow these steps:

[0081] S341, searching the calibration equipment table for the calibration equipment Ca name that is consistent with the special testing equipment "unit 1";

[0082] S342. Filter out the calibration equipment Ca names that simultaneously meet the following conditions: calibration equipment Ca measurement range > special calibration equipment SDS usage range or value, Ca maximum allowable error < (1 / 3 SDS usage allowable error), Ca measurement lower limit < SDS usage lower limit, Ca measurement upper limit > SDS usage upper limit, Ca tolerance percentage lower limit < SDS tolerance percentage lower limit, Ca tolerance percentage upper limit > SDS tolerance percentage upper limit, Ca tolerance lower limit < SDS tolerance lower limit, Ca tolerance upper limit > SDS tolerance upper limit, and construct an edge between the calibration equipment Ca name and the SDP name in the special testing equipment form.

[0083] The embodiment of the present invention also provides a knowledge graph construction system for aircraft electromechanical product parameter traceability. Figure 4 As shown, the system includes:

[0084] The form data acquisition module 401 is configured to acquire aircraft electromechanical product parameter traceability form data;

[0085] The graphic data acquisition module 402 is configured to acquire aircraft electromechanical product parameter traceability graphic data based on the aircraft electromechanical product parameter traceability form data;

[0086] The graphic data completion module 403 is configured to complete the aircraft electromechanical product parameter traceability graphic data.

[0087] In some embodiments, the aircraft electromechanical product parameter traceability form data includes an aircraft system form, an aircraft component form, a measurement unit form, a measurement parameter form, a special testing equipment form, a general testing equipment form, and a calibration equipment form.

[0088] In some embodiments, the aircraft system table includes 4 columns of data, which are: aircraft name, T0 system, T1 subsystem, and T2 subsystem;

[0089] The aircraft component form contains 12 columns of data, which are: T3 component, T3 model, T3 supplier name, T3 factory number, T3 environmental requirements, T3 test basis technical documents, T3 notes, T3 attachments, T2 subsystem name, T1 subsystem name, T0 system name, and aircraft name;

[0090] The measurement unit form contains 8 columns of data, which are: category name, unit 1, 1To2, unit 2, 2To3, unit 3, 3To4, unit 4;

[0091] The measurement parameter form contains 18 columns of data, which are: T3 name, T2 name, T1 name, T0 name, aircraft name, DP name, DP use range or value, DP use allowable error, DP use lower limit, DP use upper limit, DP tolerance lower limit, DP tolerance upper limit, DP tolerance percentage lower limit, DP tolerance percentage upper limit, DP value, DP measurement conditions, whether DP is specially tested, and unit 1;

[0092] The special detection equipment form contains 20 columns of data, which are: SDP name, SDP detection component, SDP measurement parameters, SDS name, SDS model, SDS manufacturer, SDS measurement range, SDS maximum allowable error or accuracy level, SDS remarks, SDS measurement lower limit, SDS measurement upper limit, SDS tolerance percentage lower limit, SDS tolerance percentage upper limit, SDS tolerance lower limit, SDS tolerance upper limit, SDSFS, SDS accuracy level, SDS validity period, SDS measurement conditions, unit 1;

[0093] The general testing equipment form contains 19 columns of data, which are: GD name, GD model, GD manufacturer, GD parts, GD measurement parameters, GD measurement range, GD maximum allowable error or accuracy level, GD remarks, GD measurement lower limit, GD measurement upper limit, GD tolerance percentage lower limit, GD tolerance percentage upper limit, GD tolerance lower limit, GD tolerance upper limit, GDFS, GD accuracy level, GD validity period, GD measurement conditions, unit 1;

[0094] The calibration equipment form contains 20 columns, namely: Ca name, Ca model, Ca calibration basis technical documents, Ca components, Ca measurement parameters, Ca remarks, Ca measurement range, Ca maximum allowable error or accuracy grade, Ca measurement lower limit, Ca measurement upper limit, Ca tolerance percentage lower limit, Ca tolerance percentage upper limit, Ca tolerance lower limit, Ca tolerance upper limit, CaFS, Ca accuracy grade, Ca measurement uncertainty, Ca validity period, Ca measurement conditions, unit 1.

[0095] In some embodiments, the graphic data acquisition module is further configured to:

[0096] Import the aircraft electromechanical product parameter traceability form data into a graphic database to construct aircraft electromechanical product parameter traceability graphic data; wherein, the data in the column where unit 1 in the measurement parameter, special testing equipment, general testing equipment and calibration equipment form is not imported into the graphic database, but is associated with the measurement unit form; the image data is presented in the form of node-edge-node, wherein the name of the node is set to the leftmost column of data in the aircraft electromechanical product parameter traceability form data, and the name of the edge is set according to the following method:

[0097] Aircraft system: Aircraft name - contains - Aircraft component: T2 name;

[0098] Aircraft parts: T2 name - including - measurement parameters: T3 name;

[0099] Measurement parameters: T3 name - contains - measurement unit: category name;

[0100] Special testing equipment: SDP name - testing - measurement parameters: T3 name;

[0101] General testing equipment: GD name - test - measurement parameters: T3 name;

[0102] Calibration equipment: Ca name - Calibration - General testing equipment: GD name;

[0103] Calibration equipment: Ca name - Calibration - Special testing equipment: SDP name.

[0104] In some embodiments, the graphic data edges of dedicated testing equipment: SDP name—testing—metering parameters: T3 name, general testing equipment: GD name—testing—metering parameters: T3 name, calibration equipment: Ca name—calibration—general testing equipment: GD name, calibration equipment: Ca name—calibration—dedicated testing equipment: SDP name are associated by the following method:

[0105] 1) Special testing equipment - testing - measurement parameters:

[0106] If the SDP detection component in the dedicated detection equipment form is consistent with the T3 name in the metering parameter form and the SDP measurement parameter in the dedicated detection equipment form is consistent with the DP name in the metering parameter form, then an edge between the dedicated detection equipment SDP name and the T3 name in the metering parameter form is constructed in the graph database;

[0107] 2) General testing equipment - testing - measurement parameters:

[0108] If the GD component in the general test equipment form is consistent with the T3 name in the metrology parameter form and the GD measurement parameter in the general test equipment form is consistent with the DP name in the metrology parameter form, then an edge between the general test equipment GD name and the T3 name in the metrology parameter form is constructed in the graph database;

[0109] 3) Calibration equipment - Calibration - General testing equipment:

[0110] If the Ca component in the calibration equipment form is consistent with the GD component in the general testing equipment form and the Ca measurement parameter in the calibration equipment form is consistent with the GD name in the special testing equipment form, then an edge between the calibration equipment Ca name and the GD name in the general testing equipment form is constructed in the graph database;

[0111] 4) Calibration equipment - Calibration - Special testing equipment:

[0112] If the Ca component in the calibration equipment form is consistent with the SDP component in the dedicated test equipment form and the Ca measurement parameter in the calibration equipment form is consistent with the SDP name in the dedicated test equipment form, then an edge between the calibration equipment Ca name and the SDP name in the dedicated test equipment form is constructed in the graph database.

[0113] In some embodiments, the graphic data completion module is configured by the oil pump as follows:

[0114] For general testing equipment - testing - metrology parameters, if the metrology parameters are missing general testing equipment, complete them using the following method:

[0115] In the general testing equipment form, search for the GD name of the general testing equipment whose unit 1 is consistent with the unit 1 in the measurement parameter form;

[0116] Filter out the names of general detection equipment GD that meet the first condition at the same time, and construct an edge between the names of general detection equipment GD and the names of T3 in the metrology parameter form; wherein the first condition is that the measurement range of general detection equipment GD is greater than the use range or value of metrology parameter DP, the maximum allowable error of GD is less than (1 / 3 the allowable error of metrology parameter DP use), the lower limit of GD measurement is less than the lower limit of DP use, the upper limit of GD measurement is greater than the upper limit of DP use, the lower limit of GD tolerance percentage is less than the lower limit of DP tolerance percentage, the upper limit of GD tolerance percentage is greater than the upper limit of DP tolerance percentage, the lower limit of GD tolerance is less than the lower limit of DP tolerance, and the upper limit of GD tolerance is greater than the upper limit of DP tolerance;

[0117] For dedicated testing equipment - testing - metrological parameters, if the metrological parameters are missing dedicated testing equipment, they can be completed by the following method:

[0118] Search the SDP name of the special test equipment in the special test equipment form whose unit 1 is consistent with the unit 1 in the measurement parameter form;

[0119] Filter out the SDP names of special detection equipment that meet the second condition at the same time, and construct an edge between the SDP names of special detection equipment and the T3 names in the metrology parameter form; wherein the second condition is that the measurement range of special detection equipment SDS is greater than the usage range or value of metrology parameter DP, the maximum allowable error of SDS is less than (1 / 3 the allowable error of metrology parameter DP usage), the lower limit of SDS measurement is less than the lower limit of DP usage, the upper limit of SDS measurement is greater than the upper limit of DP usage, the lower limit of SDS tolerance percentage is less than the lower limit of DP tolerance percentage, the upper limit of SDS tolerance percentage is greater than the upper limit of DP tolerance percentage, the lower limit of SDS tolerance is less than the lower limit of DP tolerance, and the upper limit of SDS tolerance is greater than the upper limit of DP tolerance;

[0120] For Calibration Equipment - Calibration - General Testing Equipment, if the general testing equipment is missing the calibration equipment, it can be completed by the following method:

[0121] In the calibration equipment form, search for the calibration equipment Ca name whose unit 1 is consistent with the unit 1 in the general testing equipment form;

[0122] Filter out the calibration equipment Ca names that simultaneously meet the third condition, and construct an edge between the calibration equipment Ca name and the GD name in the general testing equipment form; wherein the third condition is that the calibration equipment Ca measurement range>the general calibration equipment GD use range or value, the Ca maximum allowable error<(1 / 3GD use allowable error), the Ca measurement lower limit<GD use lower limit, the Ca measurement upper limit>GD use upper limit, the Ca tolerance percentage lower limit<GD tolerance percentage lower limit, the Ca tolerance percentage upper limit>GD tolerance percentage upper limit, the Ca tolerance lower limit<GD tolerance lower limit, the Ca tolerance upper limit>GD tolerance upper limit;

[0123] For calibration equipment - calibration - special test equipment, if the special test equipment is missing the calibration equipment, it can be completed by the following method:

[0124] Search for the calibration equipment Ca name whose unit 1 in the calibration equipment form is consistent with the unit 1 in the special testing equipment form;

[0125] Filter out the calibration equipment Ca names that simultaneously meet the fourth condition, and construct an edge between the calibration equipment Ca name and the SDP name in the special testing equipment form; wherein, the fourth condition is that the measurement range of the calibration equipment Ca is greater than the use range or value of the special calibration equipment SDS, the maximum allowable error of Ca is less than (1 / 3 the allowable error for use of SDS), the Ca measurement lower limit is less than the SDS use lower limit, the Ca measurement upper limit is greater than the SDS use upper limit, the Ca tolerance percentage lower limit is less than the SDS tolerance percentage lower limit, the Ca tolerance percentage upper limit is greater than the SDS tolerance percentage upper limit, the Ca tolerance lower limit is less than the SDS tolerance lower limit, and the Ca tolerance upper limit is greater than the SDS tolerance upper limit.

[0126] It should be noted that the various system structures described in this embodiment belong to the same technical concept as the previously described method, and achieve the same technical effect through the same principle, which will not be repeated here.

[0127] In addition, although exemplary embodiments have been described herein, the scope includes any and all embodiments based on the present invention with equivalent elements, modifications, omissions, combinations (e.g., various embodiments intersecting schemes), adaptations or changes. The elements in the claims will be interpreted broadly based on the language adopted in the claims, and are not limited to the examples described in this specification or during the implementation of this application, and the examples will be interpreted as non-exclusive. Therefore, this specification and examples are intended to be considered as examples only, and the true scope and spirit are indicated by the following claims and the full scope of their equivalents.

[0128] The above description is intended to be illustrative rather than restrictive. For example, the above examples (or one or more of them) can be used in combination with each other. For example, those of ordinary skill in the art can use other embodiments when reading the above description. In addition, in the above-mentioned specific embodiments, various features can be grouped together to simplify the present invention. This should not be interpreted as a feature of an invention that is not claimed for protection being necessary for any claim. On the contrary, the subject matter of the present invention may be less than all the features of the embodiments of a specific invention. Thus, the following claims are incorporated into the specific embodiments as examples or embodiments, wherein each claim is independently used as a separate embodiment, and it is considered that these embodiments can be combined with each other in various combinations or arrangements. The scope of the present invention should be determined with reference to the full scope of the equivalent forms of the appended claims and these claims.

Claims

1. A knowledge graph construction method for aircraft electromechanical product parameter traceability, characterized in that: The method comprises: Obtain aircraft electromechanical product parameter traceability form data; Based on the aircraft electromechanical product parameter traceability form data, obtaining aircraft electromechanical product parameter traceability graphic data; The aircraft electromechanical product parameter traceability graphic data is completed.

2. The method according to claim 1, characterized in that: The aircraft electromechanical product parameter traceability form data includes an aircraft system form, an aircraft component form, a measurement unit form, a measurement parameter form, a special testing equipment form, a general testing equipment form and a calibration equipment form.

3. The method according to claim 2, characterized in that The aircraft system form contains 4 columns of data, namely: aircraft name, T0 system, T1 subsystem, T2 subsystem; The aircraft component form contains 12 columns of data, which are: T3 component, T3 model, T3 supplier name, T3 factory number, T3 environmental requirements, T3 test basis technical documents, T3 notes, T3 attachments, T2 subsystem name, T1 subsystem name, T0 system name, and aircraft name; The measurement unit form contains 8 columns of data, which are: category name, unit 1, 1To2, unit 2, 2To3, unit 3, 3To4, unit 4; The measurement parameter form contains 18 columns of data, which are: T3 name, T2 name, T1 name, T0 name, aircraft name, DP name, DP use range or value, DP use allowable error, DP use lower limit, DP use upper limit, DP tolerance lower limit, DP tolerance upper limit, DP tolerance percentage lower limit, DP tolerance percentage upper limit, DP value, DP measurement conditions, whether DP is specially tested, and unit 1; The special detection equipment form contains 20 columns of data, which are: SDP name, SDP detection component, SDP measurement parameters, SDS name, SDS model, SDS manufacturer, SDS measurement range, SDS maximum allowable error or accuracy level, SDS remarks, SDS measurement lower limit, SDS measurement upper limit, SDS tolerance percentage lower limit, SDS tolerance percentage upper limit, SDS tolerance lower limit, SDS tolerance upper limit, SDSFS, SDS accuracy level, SDS validity period, SDS measurement conditions, unit 1; The general testing equipment form contains 19 columns of data, which are: GD name, GD model, GD manufacturer, GD parts, GD measurement parameters, GD measurement range, GD maximum allowable error or accuracy level, GD remarks, GD measurement lower limit, GD measurement upper limit, GD tolerance percentage lower limit, GD tolerance percentage upper limit, GD tolerance lower limit, GD tolerance upper limit, GDFS, GD accuracy level, GD validity period, GD measurement conditions, unit 1; The calibration equipment form contains 20 columns, namely: Ca name, Ca model, Ca calibration basis technical documents, Ca components, Ca measurement parameters, Ca remarks, Ca measurement range, Ca maximum allowable error or accuracy grade, Ca measurement lower limit, Ca measurement upper limit, Ca tolerance percentage lower limit, Ca tolerance percentage upper limit, Ca tolerance lower limit, Ca tolerance upper limit, CaFS, Ca accuracy grade, Ca measurement uncertainty, Ca validity period, Ca measurement conditions, unit 1.

4. The method according to claim 3, characterized in that: Based on the aircraft electromechanical product parameter traceability form data, aircraft electromechanical product parameter traceability graphic data is obtained, including: Import the aircraft electromechanical product parameter traceability form data into a graphic database to construct aircraft electromechanical product parameter traceability graphic data; wherein, the data in the column where unit 1 in the measurement parameter, special testing equipment, general testing equipment and calibration equipment form is not imported into the graphic database, but is associated with the measurement unit form; the image data is presented in the form of node-edge-node, wherein the name of the node is set to the leftmost column of data in the aircraft electromechanical product parameter traceability form data, and the name of the edge is set according to the following method: Aircraft system: Aircraft name - contains - Aircraft component: T2 name; Aircraft parts: T2 name - including - measurement parameters: T3 name; Measurement parameters: T3 name - contains - measurement unit: category name; Special testing equipment: SDP name - testing - measurement parameters: T3 name; General testing equipment: GD name - test - measurement parameters: T3 name; Calibration equipment: Ca name - Calibration - General testing equipment: GD name; Calibration equipment: Ca name - Calibration - Special testing equipment: SDP name.

5. The method according to claim 4, characterized in that Special testing equipment: SDP name - testing - measurement parameters: T3 name, general testing equipment: GD name - testing - measurement parameters: T3 name, calibration equipment: Ca name - calibration - general testing equipment: GD name, calibration equipment: Ca name - calibration - special testing equipment: The graphic data edges of the SDP name are associated in the following way: 1) Special testing equipment - testing - measurement parameters: If the SDP detection component in the dedicated detection equipment form is consistent with the T3 name in the metering parameter form and the SDP measurement parameter in the dedicated detection equipment form is consistent with the DP name in the metering parameter form, then an edge between the dedicated detection equipment SDP name and the T3 name in the metering parameter form is constructed in the graph database; 2) General testing equipment - testing - measurement parameters: If the GD component in the general test equipment form is consistent with the T3 name in the metrology parameter form and the GD measurement parameter in the general test equipment form is consistent with the DP name in the metrology parameter form, then an edge between the general test equipment GD name and the T3 name in the metrology parameter form is constructed in the graph database; 3) Calibration equipment - Calibration - General testing equipment: If the Ca component in the calibration equipment form is consistent with the GD component in the general testing equipment form and the Ca measurement parameter in the calibration equipment form is consistent with the GD name in the special testing equipment form, then an edge between the calibration equipment Ca name and the GD name in the general testing equipment form is constructed in the graph database; 4) Calibration equipment - Calibration - Special testing equipment: If the Ca component in the calibration equipment form is consistent with the SDP component in the dedicated test equipment form and the Ca measurement parameter in the calibration equipment form is consistent with the SDP name in the dedicated test equipment form, then an edge between the calibration equipment Ca name and the SDP name in the dedicated test equipment form is constructed in the graph database.

6. The method according to claim 5, characterized in that The aircraft electromechanical product parameter traceability graphic data is completed, including: For general testing equipment - testing - metrology parameters, if the metrology parameters are missing general testing equipment, complete them using the following method: In the general testing equipment form, search for the GD name of the general testing equipment whose unit 1 is consistent with the unit 1 in the measurement parameter form; Filter out the names of general detection equipment GD that meet the first condition at the same time, and construct an edge between the names of general detection equipment GD and the names of T3 in the metrology parameter form; wherein the first condition is that the measurement range of general detection equipment GD is greater than the use range or value of metrology parameter DP, the maximum allowable error of GD is less than (1 / 3 the allowable error of metrology parameter DP use), the lower limit of GD measurement is less than the lower limit of DP use, the upper limit of GD measurement is greater than the upper limit of DP use, the lower limit of GD tolerance percentage is less than the lower limit of DP tolerance percentage, the upper limit of GD tolerance percentage is greater than the upper limit of DP tolerance percentage, the lower limit of GD tolerance is less than the lower limit of DP tolerance, and the upper limit of GD tolerance is greater than the upper limit of DP tolerance; For dedicated testing equipment - testing - metrological parameters, if the metrological parameters are missing dedicated testing equipment, they can be completed by the following method: Search the SDP name of the special test equipment in the special test equipment form whose unit 1 is consistent with the unit 1 in the measurement parameter form; Filter out the SDP names of special detection equipment that meet the second condition at the same time, and construct an edge between the SDP names of special detection equipment and the T3 names in the metrology parameter form; wherein the second condition is that the measurement range of special detection equipment SDS is greater than the usage range or value of metrology parameter DP, the maximum allowable error of SDS is less than (1 / 3 the allowable error of metrology parameter DP usage), the lower limit of SDS measurement is less than the lower limit of DP usage, the upper limit of SDS measurement is greater than the upper limit of DP usage, the lower limit of SDS tolerance percentage is less than the lower limit of DP tolerance percentage, the upper limit of SDS tolerance percentage is greater than the upper limit of DP tolerance percentage, the lower limit of SDS tolerance is less than the lower limit of DP tolerance, and the upper limit of SDS tolerance is greater than the upper limit of DP tolerance; For Calibration Equipment - Calibration - General Testing Equipment, if the general testing equipment is missing the calibration equipment, it can be completed by the following method: In the calibration equipment form, search for the calibration equipment Ca name whose unit 1 is consistent with the unit 1 in the general testing equipment form; Filter out the calibration equipment Ca names that simultaneously meet the third condition, and construct an edge between the calibration equipment Ca name and the GD name in the general testing equipment form; wherein the third condition is that the calibration equipment Ca measurement range>the general calibration equipment GD use range or value, the Ca maximum allowable error<(1 / 3GD use allowable error), the Ca measurement lower limit<GD use lower limit, the Ca measurement upper limit>GD use upper limit, the Ca tolerance percentage lower limit<GD tolerance percentage lower limit, the Ca tolerance percentage upper limit>GD tolerance percentage upper limit, the Ca tolerance lower limit<GD tolerance lower limit, the Ca tolerance upper limit>GD tolerance upper limit; For calibration equipment - calibration - special test equipment, if the special test equipment is missing the calibration equipment, it can be completed by the following method: Search for the calibration equipment Ca name whose unit 1 in the calibration equipment form is consistent with the unit 1 in the special testing equipment form; Filter out the calibration equipment Ca names that simultaneously meet the fourth condition, and construct an edge between the calibration equipment Ca name and the SDP name in the special testing equipment form; wherein, the fourth condition is that the measurement range of the calibration equipment Ca is greater than the use range or value of the special calibration equipment SDS, the maximum allowable error of Ca is less than (1 / 3 the allowable error for use of SDS), the Ca measurement lower limit is less than the SDS use lower limit, the Ca measurement upper limit is greater than the SDS use upper limit, the Ca tolerance percentage lower limit is less than the SDS tolerance percentage lower limit, the Ca tolerance percentage upper limit is greater than the SDS tolerance percentage upper limit, the Ca tolerance lower limit is less than the SDS tolerance lower limit, and the Ca tolerance upper limit is greater than the SDS tolerance upper limit.

7. A knowledge graph construction system for aircraft electromechanical product parameter traceability, characterized in that: The system comprises: A form data acquisition module, configured to acquire aircraft electromechanical product parameter traceability form data; A graphic data acquisition module, configured to acquire aircraft electromechanical product parameter traceability graphic data based on the aircraft electromechanical product parameter traceability form data; The graphic data completion module is configured to complete the aircraft electromechanical product parameter traceability graphic data.

8. The system according to claim 7, characterized in that The aircraft electromechanical product parameter traceability form data includes an aircraft system form, an aircraft component form, a measurement unit form, a measurement parameter form, a special testing equipment form, a general testing equipment form and a calibration equipment form.

9. The system according to claim 8, characterized in that The aircraft system form contains 4 columns of data, namely: aircraft name, T0 system, T1 subsystem, T2 subsystem; The aircraft component form contains 12 columns of data, which are: T3 component, T3 model, T3 supplier name, T3 factory number, T3 environmental requirements, T3 test basis technical documents, T3 notes, T3 attachments, T2 subsystem name, T1 subsystem name, T0 system name, and aircraft name; The measurement unit form contains 8 columns of data, which are: category name, unit 1, 1To2, unit 2, 2To3, unit 3, 3To4, unit 4; The measurement parameter form contains 18 columns of data, which are: T3 name, T2 name, T1 name, T0 name, aircraft name, DP name, DP use range or value, DP use allowable error, DP use lower limit, DP use upper limit, DP tolerance lower limit, DP tolerance upper limit, DP tolerance percentage lower limit, DP tolerance percentage upper limit, DP value, DP measurement conditions, whether DP is specially tested, and unit 1; The special detection equipment form contains 20 columns of data, which are: SDP name, SDP detection component, SDP measurement parameters, SDS name, SDS model, SDS manufacturer, SDS measurement range, SDS maximum allowable error or accuracy level, SDS remarks, SDS measurement lower limit, SDS measurement upper limit, SDS tolerance percentage lower limit, SDS tolerance percentage upper limit, SDS tolerance lower limit, SDS tolerance upper limit, SDSFS, SDS accuracy level, SDS validity period, SDS measurement conditions, unit 1; The general testing equipment form contains 19 columns of data, which are: GD name, GD model, GD manufacturer, GD parts, GD measurement parameters, GD measurement range, GD maximum allowable error or accuracy level, GD remarks, GD measurement lower limit, GD measurement upper limit, GD tolerance percentage lower limit, GD tolerance percentage upper limit, GD tolerance lower limit, GD tolerance upper limit, GDFS, GD accuracy level, GD validity period, GD measurement conditions, unit 1; The calibration equipment form contains 20 columns, namely: Ca name, Ca model, Ca calibration basis technical documents, Ca components, Ca measurement parameters, Ca remarks, Ca measurement range, Ca maximum allowable error or accuracy grade, Ca measurement lower limit, Ca measurement upper limit, Ca tolerance percentage lower limit, Ca tolerance percentage upper limit, Ca tolerance lower limit, Ca tolerance upper limit, CaFS, Ca accuracy grade, Ca measurement uncertainty, Ca validity period, Ca measurement conditions, unit 1.

10. The system according to claim 9, characterized in that The graphic data acquisition module is further configured to: Import the aircraft electromechanical product parameter traceability form data into a graphic database to construct aircraft electromechanical product parameter traceability graphic data; wherein, the data in the column where unit 1 in the measurement parameter, special testing equipment, general testing equipment and calibration equipment form is not imported into the graphic database, but is associated with the measurement unit form; the image data is presented in the form of node-edge-node, wherein the name of the node is set to the leftmost column of data in the aircraft electromechanical product parameter traceability form data, and the name of the edge is set according to the following method: Aircraft system: Aircraft name - contains - Aircraft component: T2 name; Aircraft parts: T2 name - including - measurement parameters: T3 name; Measurement parameters: T3 name - contains - measurement unit: category name; Special testing equipment: SDP name - testing - measurement parameters: T3 name; General testing equipment: GD name - test - measurement parameters: T3 name; Calibration equipment: Ca name - Calibration - General testing equipment: GD name; Calibration equipment: Ca name - Calibration - Special testing equipment: SDP name.

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