Fuselage assembly multi-index rapid quality evaluation method based on characterization point weight

Abstract

The invention discloses a fuselage assembly multi-index rapid quality evaluation method based on characterization point weights, and the method comprises the steps: carrying out the grouping planning of fuselage characterization points according to evaluation indexes, obtaining the theoretical value of each characterization point group of a fuselage, and setting the tolerance and weight of each characterization point group; performing disorder measurement on each characterization point group of the fuselage to obtain a measurement value of each characterization point group of the fuselage; evaluating the assembly quality of the fuselage according to the measured value of each characterization point group of the fuselage corresponding to the theoretical value of each characterization point group of the fuselage to obtain an evaluation result; when the evaluation result meets the fuselage assembly quality requirement, the detection is finished; otherwise, after the fuselage parameters influencing the evaluation indexes are adjusted, the step of obtaining the evaluation result is repeatedly executed; and when the number of adjustment times is greater than a preset number, outputting evaluation results of each characterization point group of the fuselage under the current tolerance, the weight and the pose of the fuselage. The method can simplify the measurement steps, comprehensively considers each evaluation index, and improves the efficiency and reliability of fuselage quality evaluation. According to the technical scheme provided by the embodiment of the invention, the technical problems that an existing aircraft assembly quality evaluation method is tedious in measurement steps and cannot meet multiple evaluation indexes at the same time are solved.

Description

Technical Field

[0001] The present invention relates to the field of but not limited to fuselage assembly quality evaluation technology, and in particular to a fuselage assembly multi-index rapid quality evaluation method based on characterization point weights. Background Art

[0002] In aviation, aerospace and other high-precision manufacturing industries, the quality of fuselage assembly directly affects the performance and safety of the product. Therefore, in the aviation manufacturing industry, the evaluation of fuselage assembly quality is an important part of quality inspection.

[0003] Traditional assembly quality evaluation methods usually rely on a single indicator for evaluation, which is difficult to fully reflect the overall assembly quality of the fuselage. In addition, the evaluation cycle is long and the evaluation efficiency is low. Summary of the invention

[0004] Purpose of the present invention: In order to solve the above technical problems, an embodiment of the present invention provides a multi-index rapid quality evaluation method for fuselage assembly based on characterization point weights, so as to solve the problems of existing assembly quality evaluation methods, which rely on a single indicator for evaluation, making it difficult to fully reflect the overall assembly quality of the fuselage, and have a long evaluation cycle and low evaluation efficiency.

[0005] Technical solution of the present invention: In a first aspect, an embodiment of the present invention provides a multi-index rapid quality evaluation method for fuselage assembly based on characterization point weights, comprising:

[0006] Step 1: group and plan the fuselage characterization points according to the evaluation index, obtain the theoretical value of each fuselage characterization point group and set the tolerance and weight of each characterization point group;

[0007] Step 2, performing random measurements on each characterization point group of the fuselage to obtain measurement values ​​of each characterization point group of the fuselage;

[0008] Step 3, evaluating the fuselage assembly quality according to the measured values ​​of each fuselage characterization point group corresponding to the theoretical values ​​of each fuselage characterization point group, and obtaining an evaluation result;

[0009] Step 4: When the evaluation result meets the fuselage assembly quality requirements, the inspection ends; otherwise, go to step 5;

[0010] Step 5, after adjusting the fuselage parameters affecting the evaluation index, repeat steps 2 to 4; wherein adjusting the fuselage parameters affecting the evaluation index includes: adjusting the tolerance and weight of each fuselage characterization point group, and adjusting any item of the fuselage posture;

[0011] Step 6: When the number of adjustments is greater than the preset number, the evaluation results of each representative point group of the fuselage under the current tolerance, weight, and fuselage posture are output.

[0012] Optionally, in the above-mentioned method for rapid quality evaluation of fuselage assembly by multiple indexes based on characterization point weights, step 1 comprises:

[0013] Step 11, divide the fuselage characterization points into the following four groups according to the fuselage functions and characteristics:

[0014] Installation angle characterization point group: important positioning positions for the installation of the fuselage and docking components;

[0015] Symmetry characterization point group: characterization positions symmetrically distributed on the fuselage;

[0016] Horizontal plane characterization point group: characterization positions located on the horizontal plane of the fuselage;

[0017] Common characterization point group: characterization points without special classification;

[0018] Step 12, assigning tolerance and weight to each characterization point group according to the influence of each characterization point group on the overall assembly of the fuselage;

[0019] The installation angle characterization point group has the greatest impact on the overall assembly of the fuselage, and the weight is set to w1, the tolerance is a1, and the maximum tolerance is a. 1m ;

[0020] The symmetry characterization point group has the second largest influence on the overall assembly of the fuselage, and the weight is set to w2, the tolerance is a2, and the maximum tolerance is a. 2m ;

[0021] The horizontal plane characterization point group has a moderate influence on the overall assembly of the fuselage, and the weight is set to w3, the tolerance is a3, and the maximum tolerance is a. 3m ;

[0022] The common characterization point group has the least influence on the overall assembly of the fuselage, and the weight is set to w4, the tolerance is a4, and the maximum tolerance is a. 4m .

[0023] Optionally, in the above-mentioned method for rapid quality evaluation of fuselage assembly by multiple indexes based on characterization point weights, step 2 comprises:

[0024] Step 21, based on the comprehensive analysis of the measuring instrument and the assembly environment, establish the measurement coordinate system and the fuselage coordinate system respectively;

[0025] Step 22, obtaining unordered measurement values ​​of each characterization point group of the fuselage in the measurement coordinate system by unordered measurement of each characterization point group of the fuselage;

[0026] Step 23, sorting the unordered measurement values ​​of each characterization point group of the fuselage according to the measurement point alignment method to obtain the ordered measurement values ​​of each characterization point group of the fuselage in the measurement coordinate system;

[0027] Step 24, converting the ordered measurement values ​​of each characterization point group of the fuselage in the measurement coordinate system to the fuselage coordinate system according to the rigid body coordinate transformation method, to obtain the ordered measurement values ​​of each characterization point group of the fuselage in the fuselage coordinate system.

[0028] Optionally, in the above-mentioned method for rapid quality evaluation of fuselage assembly by multiple indexes based on characterization point weights, step 23 comprises:

[0029] Step 23a, calculating the distance matrix of each characterization point of the fuselage according to the unordered measurement values ​​of each characterization point group of the fuselage in the measurement coordinate system and the theoretical values ​​of each characterization point group of the fuselage; wherein the number of the unordered measurement values ​​of each characterization point group of the fuselage in the measurement coordinate system and the theoretical values ​​of each characterization point group of the fuselage are equal, but the order is inconsistent;

[0030] Step 23b, use the Hungarian algorithm to perform optimal distance matching, extract the matching results, and obtain the ordered measurement values ​​of each characterization point group of the fuselage in the measurement coordinate system; wherein, the method of the optimal distance matching is: for each characterization point group, calculate the distance between the theoretical values ​​of each pair of characterization points and sort them, then calculate the distance between the measured values ​​of each pair of characterization points, adjust the order of the measured values ​​so that the distance between each measured value corresponds to the distance between each theoretical value, thereby obtaining the sorting of the measured values ​​of each characterization point in each characterization point group.

[0031] Optionally, in the above-mentioned method for rapid quality evaluation of fuselage assembly by multiple indexes based on characterization point weights, step 3 comprises:

[0032] Step 31, obtaining the errors of each characterization point group of the fuselage according to the measured values ​​of each characterization point group of the fuselage corresponding to the theoretical values ​​of each characterization point group of the fuselage;

[0033] Step 32: evaluating the fuselage assembly quality according to the errors of each fuselage characterization point group and the corresponding tolerances and weights of each fuselage characterization point group.

[0034] Optionally, in the above-mentioned method for rapid quality evaluation of fuselage assembly by multiple indexes based on characterization point weights, step 32 comprises:

[0035] Step 321, bringing the errors of each fuselage characterization point group and the corresponding tolerances and weights of each fuselage characterization point group into the fuselage assembly quality evaluation formula for calculation;

[0036] The fuselage assembly quality evaluation formula is:

[0037]

[0038] Among them, S is the result of the fuselage posture evaluation, n is the total number of representation points in each representation point group, and w iis the weight of the i-th representation point, m i is the measured value of the i-th characterization point, t i is the theoretical value of the i-th characterization point;

[0039] Step 322, by judging whether the fuselage assembly quality evaluation result S corresponding to each fuselage characterization point group meets the fuselage assembly quality requirement S m , and get the evaluation results.

[0040] Optionally, in the above-mentioned method for rapid quality evaluation of fuselage assembly by multiple indexes based on characterization point weights, step 4 comprises:

[0041] When the evaluation result is that each fuselage assembly quality evaluation result S meets the fuselage assembly quality requirement S m , that is, S<S m , the detection is completed; otherwise, execute step 5, that is, adjust the fuselage parameters that affect the evaluation index, and repeat steps 2 to 4.

[0042] Optionally, in the above-mentioned method for rapid quality evaluation of fuselage assembly with multiple indices based on characterization point weights, the method for adjusting the fuselage parameters affecting the evaluation index in step 5 is:

[0043] Step 51, sorting the fuselage characterization point groups according to the weights of the fuselage characterization point groups;

[0044] Step 52, according to the sorting result, allocate tolerances to the characterization point groups of the fuselage; wherein the manner of allocating tolerances to the characterization point groups of the fuselage is as follows: for a characterization point group with a high weight among the characterization point groups of the fuselage, if the error of the characterization point group with a high weight exceeds the tolerance of the characterization point group, the weight of the characterization point group is reduced by one level, and the tolerance of the characterization point group is increased by a preset tolerance adjustment value a o ;

[0045] Step 53 , adjusting the posture of the fuselage according to the new tolerances of each characterization point of the fuselage obtained after tolerance allocation is performed on each characterization point group of the fuselage.

[0046] Optionally, in the above-mentioned method for rapid quality evaluation of fuselage assembly by multiple indexes based on characterization point weights, step 6 comprises:

[0047] Step 61, after adjusting the fuselage parameters that affect the evaluation index in step 5 and re-obtaining the evaluation results, when the errors of each fuselage characterization point group are less than the corresponding characterization point group tolerance, or when the number of adjustments is greater than a preset number, output the evaluation results of each fuselage characterization point group under the current tolerance, weight, and fuselage posture; the preset number is greater than 50;

[0048] Step 62: If the tolerances of each characterization point group of the fuselage are smaller than the tolerances of the corresponding characterization point groups, the detection is qualified; otherwise, the detection is unqualified.

[0049] In a second aspect, an embodiment of the present invention further provides a computer-readable storage medium, including: a memory and a processor;

[0050] The memory is configured to store executable instructions;

[0051] The processor is specifically configured to implement the fuselage assembly multi-index rapid quality evaluation method based on characterization point weights as described in any one of the above when executing the executable instructions stored in the memory.

[0052] Beneficial effects of the present invention: The embodiment of the present invention provides a multi-index rapid quality evaluation method for fuselage assembly based on the weight of the characterization point. The method establishes the concept of "group", classifies the characterization points by grouping, and simplifies the problem of repeated weight coefficient allocation for the same type of characterization points. After measuring the characteristic points, it is proposed to convert the disordered measurement values ​​into ordered measurement values ​​based on the Hungarian algorithm. The method is simple and reliable, easy to implement on site, simplifies the operation difficulty, and improves the efficiency of quality evaluation. For the situation where the evaluation results do not meet the quality requirements, it is proposed to modify the tolerance, weight and other methods for optimization iteration, so that the assembly error is gradually reduced, and the problem of random iteration in the current assembly is solved. In general, the multi-index rapid quality evaluation method for fuselage assembly provided by the embodiment of the present invention can realize the accurate description of the assembly process, solve the problem that the personal production habits or level of the operator affect the assembly process and quality in the current production process; an innovative method is used to quantitatively analyze the calculation and feedback methods of the assembly index, and realize multi-index rapid quality evaluation. BRIEF DESCRIPTION OF THE DRAWINGS

[0053] The accompanying drawings are used to provide a further understanding of the technical solution of the present invention and constitute a part of the specification. Together with the embodiments of the present application, they are used to explain the technical solution of the present invention and do not constitute a limitation on the technical solution of the present invention.

[0054] Figure 1 An overall flow chart of a method for rapid quality evaluation of fuselage assembly using multiple indices based on characterization point weights provided by an embodiment of the present invention;

[0055] Figure 2 is a schematic diagram of fuselage characterization point groups divided according to fuselage functions and characteristics in an embodiment of the present invention;

[0056] Figure 3 Schematic diagram of the aircraft fuselage characterization point measurement process in an embodiment of the present invention;

[0057] Figure 4This is a flowchart of sorting unordered measurement values ​​of aircraft fuselage characterization points in an embodiment of the present invention. DETAILED DESCRIPTION

[0058] In order to make the purpose, technical solution and advantages of the present invention more clear, the embodiments of the present invention will be described in detail with reference to the accompanying drawings. It should be noted that the embodiments and features in the embodiments of the present application can be combined with each other arbitrarily without conflict.

[0059] The above background technology has explained the necessity of evaluating the quality of fuselage assembly based on its important impact on product performance and safety. However, the traditional assembly quality evaluation method usually relies on a single indicator for evaluation, which is difficult to fully reflect the overall assembly quality of the fuselage, and the evaluation cycle is long and the evaluation efficiency is low.

[0060] In view of the above problems, it is urgent to provide a method that can quickly, accurately and comprehensively evaluate the quality of fuselage assembly with multiple indicators to improve the assembly quality and detection efficiency. Based on this demand, an embodiment of the present invention provides a method for rapid quality evaluation of fuselage assembly with multiple indicators based on characterization point weights. This method achieves rapid evaluation of fuselage assembly quality and improves detection efficiency and accuracy by grouping and weighting characterization points, combining disordered measurement and error analysis.

[0061] The present invention provides the following specific embodiments which can be combined with each other. The same or similar concepts or processes may not be described in detail in some embodiments.

[0062] Figure 1 The overall flow chart of a method for rapid quality evaluation of fuselage assembly with multiple indices based on characterization point weights provided by an embodiment of the present invention. The method for rapid quality evaluation of fuselage assembly with multiple indices provided by an embodiment of the present invention comprises the following steps:

[0063] Step 1: group and plan the fuselage characterization points according to the evaluation index, obtain the theoretical value of each fuselage characterization point group and set the tolerance and weight of each characterization point group;

[0064] Step 2, performing random measurements on each characterization point group of the fuselage to obtain measurement values ​​of each characterization point group of the fuselage;

[0065] Step 3, evaluating the fuselage assembly quality according to the measured values ​​of each fuselage characterization point group corresponding to the theoretical values ​​of each fuselage characterization point group, and obtaining an evaluation result;

[0066] Step 4: When the evaluation result meets the fuselage assembly quality requirements, the inspection ends; otherwise, go to step 5;

[0067] Step 5, after adjusting the fuselage parameters affecting the evaluation index, repeat steps 2 to 4; wherein adjusting the fuselage parameters affecting the evaluation index includes: adjusting the tolerance and weight of each fuselage characterization point group, and adjusting any item of the fuselage posture;

[0068] Step 6: When the number of adjustments is greater than the preset number, the evaluation results of each representative point group of the fuselage under the current tolerance, weight, and fuselage posture are output.

[0069] In one implementation of the embodiment of the present invention, Figure 2 The figure is a schematic diagram of the fuselage characterization point groups divided according to the fuselage functions and characteristics in the embodiment of the present invention. The implementation method of grouping and planning the fuselage characterization points according to the evaluation index in the above step 1, obtaining the theoretical value of each fuselage characterization point group and setting the tolerance and weight of each characterization point group includes the following steps:

[0070] Step 11, divide the fuselage characterization points into the following four groups according to the fuselage functions and characteristics:

[0071] Installation angle characterization point group: important positioning positions for the installation of the fuselage and docking components;

[0072] Symmetry characterization point group: characterization positions symmetrically distributed on the fuselage;

[0073] Horizontal plane characterization point group: characterization positions located on the horizontal plane of the fuselage;

[0074] Common characterization point group: Characterization points without special classification; such as Figure 2 The characterization point groups shown.

[0075] Step 12, assigning tolerance and weight to each characterization point group according to the influence of each characterization point group on the overall assembly of the fuselage;

[0076] In this implementation, the installation angle characterization point group has the greatest impact on the overall assembly of the fuselage, and the weight is set to w1, the tolerance is a1, and the maximum tolerance is a. 1m ;

[0077] The symmetry characterization point group has the second largest influence on the overall assembly of the fuselage. The weight is set to w2, the tolerance is a2, and the maximum tolerance is a. 2m ;

[0078] The horizontal plane characterization point group has a medium influence on the overall assembly of the fuselage. The weight is set to w3, the tolerance is a3, and the maximum tolerance is a. 3m ;

[0079] The common characterization point group has the least influence on the overall assembly of the fuselage. The weight is set to w4, the tolerance is a4, and the maximum tolerance is a 4m .

[0080] In an implementation of the embodiment of the present invention, the implementation method of performing disorderly measurement on each characterization point group of the fuselage in the above step 2 to obtain the measurement value of each characterization point group of the fuselage includes the following steps:

[0081] Step 21, based on the comprehensive analysis of the measuring instrument and the assembly environment, establish a measurement coordinate system and a fuselage coordinate system respectively; this embodiment uses a laser tracker for measurement and quality evaluation;

[0082] In this step, set up the measurement coordinate system T m , fuselage coordinate system T b T o .

[0083] Step 22, by performing disordered measurement on each characterization point group of the fuselage, such as Figure 3 As shown, the unordered measurement values ​​of each characterization point group of the fuselage in the measurement coordinate system are obtained.

[0084] In this implementation, all fuselage characterization point groups can be measured in any order to obtain the unordered measurement values ​​of the fuselage characterization point groups {P us}.

[0085] Step 23, sorting the unordered measurement values ​​of each characterization point group of the fuselage according to the measurement point alignment method to obtain the ordered measurement values ​​of each characterization point group of the fuselage in the measurement coordinate system.

[0086] In this implementation, the unordered measurement values ​​of the fuselage characterization point group {P us}According to the theoretical value of the fuselage characterization point group {P l} are sorted in order to obtain the measurement coordinate system T m The ordered measurement values ​​of the fuselage characterization point group {P s}.

[0087] Step 24, converting the ordered measurement values ​​of each characterization point group of the fuselage in the measurement coordinate system to the fuselage coordinate system according to the rigid body coordinate transformation method, to obtain the ordered measurement values ​​of each characterization point group of the fuselage in the fuselage coordinate system.

[0088] The rigid body coordinate transformation method in this step can be expressed by the coordinate transformation matrix equation:

[0089]

[0090] in, Represents the measurement coordinate system T m and the reference coordinate system T o The coordinate transformation matrix between Represents the reference coordinate system T o and fuselage coordinate system T bThe coordinate transformation matrix between

[0091] In this implementation, the measurement coordinate system T m The ordered measurement values ​​of each representative point group of the fuselage under {P s}The measured values ​​of the fuselage characterization point group are obtained through rigid body coordinate transformation {P m}.

[0092] In an implementation case of this implementation method, in the above step 23, the unordered measurement values ​​of the fuselage characterization point group are sorted according to the measurement point alignment method to obtain the ordered measurement values ​​of the fuselage characterization point group in the measurement coordinate system, including the following steps:

[0093] Step 23a, calculating the distance matrix of each characterization point of the fuselage according to the unordered measurement values ​​of each characterization point group of the fuselage in the measurement coordinate system and the theoretical values ​​of each characterization point group of the fuselage; the unordered measurement values ​​of each characterization point group of the fuselage in the measurement coordinate system and the theoretical values ​​of each characterization point group of the fuselage are equal in number, but inconsistent in order.

[0094] In this embodiment, according to the measurement coordinate system T m The unordered measurement values ​​of the fuselage characterization point group under {P us} and the theoretical value of the fuselage characterization point group {P l}Calculate the distance matrix of the characterization points

[0095]

[0096] Where i, j represent the unordered measurement values ​​of the fuselage characterization point group {P us} and the theoretical value of the fuselage characterization point group {P l}The number of rows and columns; represents the unordered measurement value of the fuselage characterization point group {P us} and the theoretical value of the fuselage characterization point group {P l The distance between the representation points at corresponding positions in}.

[0097] Step 23b, using the Hungarian algorithm to perform distance optimal matching, extracting the matching results, and obtaining the ordered measurement values ​​of each representative point group of the fuselage in the measurement coordinate system, such as Figure 4 The figure shows a flowchart of sorting unordered measurement values ​​of aircraft fuselage characterization points in an embodiment of the present invention. The optimal distance matching method in this step is: for each characterization point group, the distance between the theoretical values ​​of each characterization point is calculated and sorted, and then the distance between the measured values ​​of each characterization point is calculated, and the order of the measured values ​​is adjusted so that the distance between each measured value corresponds to the distance between each theoretical value, thereby obtaining the sorting of the measured values ​​of each characterization point in each characterization point group.

[0098] In this embodiment, the distance matrix of the characterization points is solved by the Hungarian algorithm. The unordered measurement value of the fuselage characterization point group {P us} and the theoretical value of the fuselage characterization point group {P l}, the order of the fuselage characterization point group measurement values ​​when the distance between the characterization points is the smallest, and this order is set as the measurement coordinate system T m The ordered measurement values ​​of the fuselage characterization point group {P s}.

[0099] In an implementation of the embodiment of the present invention, the method of evaluating the fuselage assembly quality according to the fuselage characterization point group theoretical value and the fuselage characterization point group measured value in the above step 3 to obtain the evaluation result includes the following steps:

[0100] Step 31, according to the measured values ​​of each fuselage characterization point group corresponding to the theoretical values ​​of each fuselage characterization point group, obtain the fuselage characterization point group error. l}The corresponding measurement values ​​of each representative point group of the fuselage {P m}Get the error {δ o}for:

[0101] {δ o}={P l}-{P m};

[0102] Step 32: evaluating the fuselage assembly quality according to the errors of each fuselage characterization point group and the corresponding tolerances and weights of each fuselage characterization point group.

[0103] In this implementation, the tolerance {w} and weight {a} of each characterization point group of the fuselage are as follows: the weight of the mounting hole where the fuselage connects to the wing root is w1, the tolerance is a1, and the maximum tolerance is a 1m ; The weight of the center point of the portholes on both sides of the fuselage is w2, the tolerance is a2, and the maximum tolerance is a 2m ; The weight of the support point at the bottom of the fuselage is w3, the tolerance is a3, and the maximum tolerance is a 3m The bolt hole weight on the fuselage surface is w4, the tolerance is a4, and the maximum tolerance is a 4m .

[0104] In one implementation case of this implementation, in step 32, the fuselage assembly quality is evaluated according to the error of each fuselage characterization point group and the corresponding tolerance and weight of each fuselage characterization point group, including the following steps:

[0105] Step 321, bringing the errors of each fuselage characterization point group and the corresponding tolerances and weights of each fuselage characterization point group into the fuselage assembly quality evaluation formula for calculation;

[0106] The fuselage assembly quality evaluation formula is:

[0107]

[0108] Among them, S is the result of the fuselage posture evaluation, n is the total number of representation points in each representation point group, and w i is the weight of the i-th representation point, m i is the measured value of the i-th characterization point, t i is the theoretical value of the i-th characterization point.

[0109] Step 322, by judging whether the fuselage assembly quality evaluation result S corresponding to each fuselage characterization point group meets the fuselage assembly quality requirement S m , and get the evaluation results.

[0110] In one implementation of the embodiment of the present invention, the judgment method of the above step 4 is: when the evaluation result is that each fuselage assembly quality evaluation result S meets the fuselage assembly quality requirement S m , that is, S<S m , the detection is completed; otherwise, execute step 5, that is, adjust the fuselage parameters that affect the evaluation index, and repeat steps 2 to 4.

[0111] In an implementation of the embodiment of the present invention, the adjustment of the fuselage parameters affecting the evaluation index in the above step 5 includes the following steps:

[0112] Step 51, sorting the fuselage characterization point groups according to the weights of the fuselage characterization point groups;

[0113] Step 52, according to the sorting result, allocate tolerances to the characterization point groups of the fuselage; wherein the manner of allocating tolerances to the characterization point groups of the fuselage is as follows: for a characterization point group with a high weight among the characterization point groups of the fuselage, if the error of the characterization point group with a high weight exceeds the tolerance of the characterization point group, the weight of the characterization point group is reduced by one level, and the tolerance of the characterization point group is increased by a preset tolerance adjustment value;

[0114] Step 53: adjusting the posture of the fuselage according to the tolerances of the new fuselage characterization points obtained after the tolerances of the fuselage characterization point groups are allocated.

[0115] Furthermore, the method for rapid quality evaluation of fuselage assembly with multiple indices provided in the embodiment of the present invention, after adjusting the fuselage parameters affecting the evaluation indices, performs step 6 including:

[0116] Step 61, after adjusting the fuselage parameters that affect the evaluation index in step 5 and re-obtaining the evaluation results, when the errors of each fuselage characterization point group are less than the corresponding characterization point group tolerance, or when the number of adjustments is greater than a preset number, output the evaluation results of each fuselage characterization point group under the current tolerance, weight, and fuselage posture; the preset number is greater than 50;

[0117] Step 62: If the tolerances of the characterization point groups of the fuselage are all smaller than the tolerances of the corresponding characterization point groups, the detection is qualified; otherwise, the detection is unqualified.

[0118] In a specific implementation of the embodiment of the present invention, the specific implementation scheme of adjusting the fuselage parameters affecting the evaluation index in step 5 may include the following steps:

[0119] Step 51: According to the weights {w} of each body characterization point group, {P l} to sort;

[0120] The order of this step is, for example: the weight of the mounting hole where the fuselage connects to the wing root is w1; the weight of the center point of the portholes on both sides of the fuselage is w2; the weight of the support point at the bottom of the fuselage is w3; the weight of the bolt hole on the surface of the fuselage is w4,

[0121] w1>w2>w3>w4

[0122] Get the fuselage characterization point group {P l} are sorted as follows:

[0123] {P l}={P l1 , P l2 , P l3 , P l4};

[0124] Step 52, according to the sorting result, allocating tolerances to each characterization point group of the fuselage;

[0125] In this step, the tolerance allocation method for the fuselage characterization point group is as follows: for the characterization point group with a high weight among the fuselage characterization point groups, if the error of the characterization point group with a high weight exceeds the tolerance of the characterization point group, the weight of the characterization point group is reduced by one level, and the tolerance of the characterization point group is increased by the preset tolerance adjustment value a o .

[0126] Assume that in this embodiment, the characterization point group error corresponding to the fuselage characterization point group weight w2 exceeds the corresponding characterization point group tolerance a1, then the characterization point group tolerance a2 corresponding to the characterization point group weight w2 is increased by a o , that is:

[0127] a2=a′2+a o

[0128] Wherein, a′2 represents the tolerance of the representation point group before adjustment corresponding to the representation point group weight w2, and a2 represents the tolerance of the representation point group after adjustment corresponding to the representation point group weight w2.

[0129] Step 53, adjusting the posture of the fuselage according to the tolerance of each new fuselage characterization point obtained after the tolerance is allocated to each characterization point group of the fuselage;

[0130] Step 54, after adjusting the fuselage parameters that affect the evaluation index, repeat the step of obtaining the evaluation result, that is, repeat step 2 to step 4.

[0131] Step 61, after adjusting the fuselage parameters that affect the evaluation index in step 5 and re-obtaining the evaluation results, until the errors of each fuselage characterization point group are less than the corresponding characterization point group tolerance, or when the number of adjustments is greater than a preset number, output the evaluation results of each fuselage characterization point group under the current tolerance, weight, and fuselage posture.

[0132] In this embodiment, after the first measurement and evaluation of the fuselage posture is performed according to the obtained evaluation results, it is found that the fuselage characterization point group error of the weight w1 of the fuselage characterization point group is The corresponding characterization point group tolerance a1 is exceeded. After adjusting the tolerance, a second measurement evaluation is performed and it is found that the characterization point group error of the fuselage characterization point group weight w2 If the error exceeds the corresponding characterization point group tolerance a2, the characterization point group tolerance a2 is further adjusted; after the tolerance is adjusted, a second measurement evaluation is performed, and it is found that the error of each characterization point group of the fuselage is less than the corresponding fuselage characterization point group tolerance.

[0133] Step 62: If the tolerances of all fuselage characterization point groups are smaller than the corresponding fuselage characterization point group tolerances, the test is qualified; otherwise, the test is unqualified. In an embodiment, if the tolerances of all fuselage characterization point groups are smaller than the corresponding fuselage characterization point group maximum tolerances, the test is qualified.

[0134] In an optional embodiment, the preset number of times of adjusting the fuselage parameters is greater than 50.

[0135] The embodiment of the present invention provides a multi-index rapid quality evaluation method for fuselage assembly. The method establishes the concept of "group", classifies the characterization points in a grouping manner, and simplifies the problem of repeated weight coefficient allocation for the same type of characterization points. After measuring the feature points, it is proposed to convert the disordered measurement values ​​into ordered measurement values ​​based on the Hungarian algorithm. The method is simple and reliable, easy to implement on site, simplifies the operation difficulty, and improves the efficiency of quality evaluation. For the situation where the evaluation results do not meet the quality requirements, it is proposed to modify the tolerance, weight and other methods for optimization iteration, so that the assembly error is gradually reduced, and the problem of random iteration in the current assembly is solved. In general, the multi-index rapid quality evaluation method for fuselage assembly provided by the embodiment of the present invention can realize the accurate description of the assembly process, solve the problem that the personal production habits or levels of operators in the current production process affect the assembly process and quality; an innovative method is used to quantitatively analyze the calculation and feedback methods of the assembly indicators, and realize multi-index rapid quality evaluation.

[0136] Based on the fuselage assembly multi-index rapid quality evaluation method based on characterization point weights provided by the above-mentioned embodiment of the present invention, the embodiment of the present invention further provides a computer-readable storage medium, including: a memory and a processor;

[0137] The memory is configured to store executable instructions;

[0138] The processor is specifically configured to implement the fuselage assembly multi-index rapid quality evaluation method based on characterization point weights as provided in any of the above embodiments when executing the executable instructions stored in the memory.

[0139] Although the embodiments disclosed in the present invention are as above, the contents are only embodiments adopted to facilitate understanding of the present invention and are not intended to limit the present invention. Any technician in the field to which the present invention belongs can make any modifications and changes in the form and details of implementation without departing from the spirit and scope disclosed in the present invention, but the patent protection scope of the present invention shall still be subject to the scope defined in the attached claims.

Claims

1. A multi-index rapid quality evaluation method for fuselage assembly based on characterization point weights, characterized in that: The method comprises: Step 1: group and plan the fuselage characterization points according to the evaluation index, obtain the theoretical value of each fuselage characterization point group and set the tolerance and weight of each characterization point group; Step 2, performing random measurements on each characterization point group of the fuselage to obtain measurement values ​​of each characterization point group of the fuselage; Step 3, evaluating the fuselage assembly quality according to the measured values ​​of each fuselage characterization point group corresponding to the theoretical values ​​of each fuselage characterization point group, and obtaining an evaluation result; Step 4: When the evaluation result meets the fuselage assembly quality requirements, the inspection ends; otherwise, go to step 5; Step 5, after adjusting the fuselage parameters affecting the evaluation index, repeat steps 2 to 4; wherein adjusting the fuselage parameters affecting the evaluation index includes: adjusting the tolerance and weight of each fuselage characterization point group, and adjusting any item of the fuselage posture; Step 6: When the number of adjustments is greater than the preset number, the evaluation results of each representative point group of the fuselage under the current tolerance, weight, and fuselage posture are output.

2. The method for rapid quality evaluation of fuselage assembly based on multiple indexes based on characterization point weights according to claim 1 is characterized in that: The step 1 comprises: Step 11, divide the fuselage characterization points into the following four groups according to the fuselage functions and characteristics: Installation angle characterization point group: important positioning positions for the installation of the fuselage and docking components; Symmetry characterization point group: characterization positions symmetrically distributed on the fuselage; Horizontal plane characterization point group: characterization positions located on the horizontal plane of the fuselage; Common characterization point group: characterization points without special classification; Step 12, assigning tolerance and weight to each characterization point group according to the influence of each characterization point group on the overall assembly of the fuselage; The installation angle characterization point group has the greatest impact on the overall assembly of the fuselage, and the weight is set to w1, the tolerance is a1, and the maximum tolerance is a. 1m ; The symmetry characterization point group has the second largest influence on the overall assembly of the fuselage, and the weight is set to w2, the tolerance is a2, and the maximum tolerance is a. 2m ; The horizontal plane characterization point group has a moderate influence on the overall assembly of the fuselage, and the weight is set to w3, the tolerance is a3, and the maximum tolerance is a. 3m ; The common characterization point group has the least influence on the overall assembly of the fuselage, and the weight is set to w4, the tolerance is a4, and the maximum tolerance is a. 4m .

3. The method for rapid quality evaluation of fuselage assembly based on multiple indexes based on characterization point weights according to claim 1 is characterized in that: The step 2 comprises: Step 21, based on the comprehensive analysis of the measuring instrument and the assembly environment, establish the measurement coordinate system and the fuselage coordinate system respectively; Step 22, obtaining unordered measurement values ​​of each characterization point group of the fuselage in the measurement coordinate system by unordered measurement of each characterization point group of the fuselage; Step 23, sorting the unordered measurement values ​​of each characterization point group of the fuselage according to the measurement point alignment method to obtain the ordered measurement values ​​of each characterization point group of the fuselage in the measurement coordinate system; Step 24, converting the ordered measurement values ​​of each characterization point group of the fuselage in the measurement coordinate system to the fuselage coordinate system according to the rigid body coordinate transformation method, to obtain the ordered measurement values ​​of each characterization point group of the fuselage in the fuselage coordinate system.

4. The method for rapid quality evaluation of fuselage assembly based on multiple indexes based on characterization point weights according to claim 3 is characterized in that: The step 23 comprises: Step 23a, calculating the distance matrix of each characterization point of the fuselage according to the unordered measurement values ​​of each characterization point group of the fuselage in the measurement coordinate system and the theoretical values ​​of each characterization point group of the fuselage; wherein the number of the unordered measurement values ​​of each characterization point group of the fuselage in the measurement coordinate system and the theoretical values ​​of each characterization point group of the fuselage are equal, but the order is inconsistent; Step 23b, use the Hungarian algorithm to perform optimal distance matching, extract the matching results, and obtain the ordered measurement values ​​of each characterization point group of the fuselage in the measurement coordinate system; wherein, the method of the optimal distance matching is: for each characterization point group, calculate the distance between the theoretical values ​​of each pair of characterization points and sort them, then calculate the distance between the measured values ​​of each pair of characterization points, adjust the order of the measured values ​​so that the distance between each measured value corresponds to the distance between each theoretical value, thereby obtaining the sorting of the measured values ​​of each characterization point in each characterization point group.

5. The method for rapid quality evaluation of fuselage assembly based on multiple indexes of characterization point weights according to claim 1 is characterized in that: The step 3 comprises: Step 31, obtaining the errors of each characterization point group of the fuselage according to the measured values ​​of each characterization point group of the fuselage corresponding to the theoretical values ​​of each characterization point group of the fuselage; Step 32: evaluating the fuselage assembly quality according to the errors of each fuselage characterization point group and the corresponding tolerances and weights of each fuselage characterization point group.

6. The method for rapid quality evaluation of fuselage assembly based on multiple indexes based on characterization point weights according to claim 5 is characterized in that: The step 32 comprises: Step 321, bringing the errors of each fuselage characterization point group and the corresponding tolerances and weights of each fuselage characterization point group into the fuselage assembly quality evaluation formula for calculation; The fuselage assembly quality evaluation formula is: Among them, S is the result of the fuselage posture evaluation, n is the total number of representation points in each representation point group, and w i is the weight of the i-th representation point, m i is the measured value of the i-th characterization point, t i is the theoretical value of the i-th characterization point; Step 322, by judging whether the fuselage assembly quality evaluation result S corresponding to each fuselage characterization point group meets the fuselage assembly quality requirement S m , and get the evaluation results.

7. The method for rapid quality evaluation of fuselage assembly based on multiple indexes based on characterization point weights according to claim 6 is characterized in that: The step 4 comprises: When the evaluation result is that each fuselage assembly quality evaluation result S meets the fuselage assembly quality requirement S n , that is, S<S m , the detection is completed; otherwise, execute step 5, that is, adjust the fuselage parameters that affect the evaluation index, and repeat steps 2 to 4.

8. The method for rapid quality evaluation of fuselage assembly based on multiple indexes based on characterization point weights according to claim 6 is characterized in that: The method of adjusting the fuselage parameters affecting the evaluation index in step 5 is: Step 51, sorting the fuselage characterization point groups according to the weights of the fuselage characterization point groups; Step 52, according to the sorting result, allocate tolerances to the characterization point groups of the fuselage; wherein the manner of allocating tolerances to the characterization point groups of the fuselage is as follows: for a characterization point group with a high weight among the characterization point groups of the fuselage, if the error of the characterization point group with a high weight exceeds the tolerance of the characterization point group, the weight of the characterization point group is reduced by one level, and the tolerance of the characterization point group is increased by a preset tolerance adjustment value a o ; Step 53 , adjusting the posture of the fuselage according to the new tolerances of each characterization point of the fuselage obtained after tolerance allocation is performed on each characterization point group of the fuselage.

9. The method for rapid quality evaluation of fuselage assembly based on multiple indexes based on characterization point weights according to claim 8, characterized in that: The step 6 comprises: Step 61, after adjusting the fuselage parameters that affect the evaluation index in step 5 and re-obtaining the evaluation results, when the errors of each fuselage characterization point group are less than the corresponding characterization point group tolerance, or when the number of adjustments is greater than a preset number, output the evaluation results of each fuselage characterization point group under the current tolerance, weight, and fuselage posture; the preset number is greater than 50; Step 62: If the tolerances of each characterization point group of the fuselage are smaller than the tolerances of the corresponding characterization point groups, the detection is qualified; otherwise, the detection is unqualified.

10. A computer-readable storage medium, characterized in that: include: Memory and processor; The memory is configured to store executable instructions; The processor is specifically configured to implement the fuselage assembly multi-index rapid quality evaluation method based on characterization point weights as described in any one of claims 1 to 9 when executing the executable instructions stored in the memory.

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