Driving design method and device for aircraft skin simulation module surface and storage medium

Abstract

The embodiment of the invention discloses a drive design method and device for an aircraft skin simulation module surface and a storage medium. The method comprises the steps that a to-be-designed part is acquired, and design characteristic parameters of the to-be-designed part are extracted; designing characteristic parameters including a curved surface, an inner hole and a concave area; obtaining an aircraft skin simulation modular surface design knowledge base, and determining similar skin parts of the to-be-designed part in the aircraft skin simulation modular surface design knowledge base according to the design characteristic parameters; extracting design knowledge and design rules of similar skin parts from the aircraft skin simulation modular surface design knowledge base; and performing drive design on the to-be-designed part according to the design knowledge and the design rule to obtain a target design part. According to the method, driving design of a new skin part die surface can be carried out based on design knowledge and design rules of the completed skin part, skin part design can be automatically carried out, and manpower needed by design is reduced.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft manufacturing, and in particular to a driving design method, device and storage medium of an aircraft skin simulation form surface. BACKGROUND

[0002] In the simulation design of an aircraft skin, the design parameters, process parameters and design requirements of the aircraft skin form surface are usually set by the design experience of a designer.

[0003] There is a lack of unified design standard for the simulation design of an aircraft skin, and the automatic design of an aircraft skin part cannot be realized. SUMMARY

[0004] The present application provides a driving design method, device and storage medium of an aircraft skin simulation form surface, to automatically design a skin part and reduce the manpower required for design.

[0005] According to an aspect of the present application, a driving design method of an aircraft skin simulation form surface is provided, which comprises:

[0006] acquiring a part to be designed and extracting design feature parameters of the part to be designed; the design feature parameters comprise a curved surface, an inner hole and a recessed area;

[0007] acquiring an aircraft skin simulation form surface design knowledge base and determining a similar skin part of the part to be designed in the aircraft skin simulation form surface design knowledge base according to the design feature parameters;

[0008] extracting design knowledge and design rules of the similar skin part in the aircraft skin simulation form surface design knowledge base;

[0009] driving design of the part to be designed according to the design knowledge and design rules to obtain a target design part.

[0010] According to another aspect of the present application, a driving design device of an aircraft skin simulation form surface is provided, which comprises:

[0011] a design feature parameter extraction module for acquiring a part to be designed and extracting design feature parameters of the part to be designed; the design feature parameters comprise a curved surface, an inner hole and a recessed area;

[0012] a similar skin part determination module for acquiring an aircraft skin simulation form surface design knowledge base and determining a similar skin part of the part to be designed in the aircraft skin simulation form surface design knowledge base according to the design feature parameters;

[0013] The design knowledge extraction module is configured to extract design knowledge and design rules of the similar skin part from the aircraft skin simulation surface design knowledge base.

[0014] The driving design module is configured to drive design of the part to be designed according to the design knowledge and the design rules, so as to obtain a target design part.

[0015] According to another aspect of the present application, an electronic device is provided, which comprises:

[0016] at least one processor; and

[0017] a memory connected with the at least one processor; wherein

[0018] The memory stores a computer program executable by the at least one processor, and the computer program is executed by the at least one processor to enable the at least one processor to execute the driving design method of the aircraft skin simulation surface according to any one of the embodiments of the present application.

[0019] According to another aspect of the present application, a computer readable storage medium is provided, which stores computer instructions for enabling a processor to implement the driving design method of the aircraft skin simulation surface according to any one of the embodiments of the present application when executed by the processor.

[0020] According to another aspect of the present application, a computer program product is provided, which comprises a computer program for implementing the driving design method of the aircraft skin simulation surface according to any one of the embodiments of the present application when executed by a processor.

[0021] The technical solution of the embodiments of the present application comprises the following steps: obtaining a part to be designed, and extracting design feature parameters of the part to be designed; the design feature parameters comprise a curved surface, an inner hole and a recessed area; obtaining an aircraft skin simulation surface design knowledge base, and determining a similar skin part of the part to be designed in the aircraft skin simulation surface design knowledge base according to the design feature parameters; extracting design knowledge and design rules of the similar skin part from the aircraft skin simulation surface design knowledge base; and driving design of the part to be designed according to the design knowledge and the design rules, so as to obtain a target design part. The driving design problem of the aircraft skin part is solved, the driving design of a new skin part surface can be performed based on the design knowledge and the design rules of the skin part which has been designed, the skin part design can be automatically performed, and the manpower required for design is reduced.

[0022] It should be understood that the content described in this part is not intended to identify key or important features of the embodiments of the present application, nor to limit the scope of the present application. Other features of the present application will become apparent from the following description. BRIEF DESCRIPTION OF DRAWINGS

[0023] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the accompanying drawings needed to be used in the embodiments description will be briefly introduced. Obviously, the accompanying drawings in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can be obtained based on these drawings without any creative effort.

[0024] Figure 1 is a flow chart of a driving design method of an aircraft skin simulation die provided by the embodiment one of the present application;

[0025] Figure 2 is a schematic diagram of a driving design knowledge base of an aircraft skin simulation die provided by the embodiment one of the present application;

[0026] Figure 3 is a driving design flow chart of a skin part provided by the embodiment one of the present application;

[0027] Figure 4 is a flow chart of a driving design method of an aircraft skin simulation die provided by the embodiment two of the present application;

[0028] Figure 5 is a structural schematic diagram of a driving design device of an aircraft skin simulation die provided by the embodiment three of the present application;

[0029] Figure 6 is a structural schematic diagram of an electronic device for implementing the driving design method of an aircraft skin simulation die. DETAILED DESCRIPTION

[0030] In order to make the technical personnel in the art better understand the present application, the technical solutions in the embodiments of the present application will be described clearly and completely in the following with reference to the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only some embodiments of the present application, but not all. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without any creative effort should belong to the scope of protection of the present application.

[0031] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and in the above drawings are used to distinguish similar objects, and do not necessarily have to be used to describe a specific order or sequence. It should be understood that the data thus used can be interchanged under appropriate circumstances, so that the embodiments of the application described herein can be implemented in an order other than that illustrated or described herein. In addition, the terms "include" and "have" and any variations thereof are intended to cover non-exclusive inclusion, for example, a process, method, system, product or device including a series of steps or units does not have to be limited to only those steps or units clearly listed, but can include other steps or units not clearly listed or inherent to these processes, methods, products or devices.

[0032] Embodiment one

[0033] Figure 1 It is a flowchart of a driving design method of an aircraft skin simulation die provided according to the embodiment one of the present application. The embodiment can be applicable to the driving design of the aircraft skin stretching die surface in the process design stage of the aircraft skin part. The method can be executed by a driving design device of the aircraft skin simulation die. The driving design device of the aircraft skin simulation die can be realized in the form of hardware and / or software, and can be configured in an electronic device such as a computer. As shown in the figure, the method comprises: Figure 1

[0034] Step 110, obtaining a part to be designed, and extracting design feature parameters of the part to be designed.

[0035] The design features can be the stretching forming features in the part to be designed, such as the shape features of the part and the process design information such as the wrapping angle of the part. Specifically, the design feature parameters can include curved surfaces, inner holes and recessed areas.

[0036] The design feature parameter extraction of the part to be designed can be feature recognition and recording of the parameters required to form the features.

[0037] Step 120, obtaining an aircraft skin simulation die design knowledge base, and determining similar skin parts of the part to be designed in the aircraft skin simulation die design knowledge base according to the design feature parameters.

[0038] In the embodiment of the present application, the aircraft skin simulation die design knowledge base can be a knowledge base formed according to the design information of the completed skin parts. The aircraft skin simulation die design knowledge base can include the design knowledge of the aircraft skin part simulation die, the stretching feature parameters of the aircraft skin part, the design parameters of the aircraft skin die, the design feature parameters, the general knowledge rules of the skin die design and the design rules applicable to the skin parts. The general knowledge rules can include design specifications.​

[0039] In the determination of similar skin parts in the aircraft skin simulation die face design knowledge base, the similarity of the to-be-designed part and each skin part in the library can be determined according to the design feature parameters. The skin part with the highest similarity is taken as the similar skin part of the to-be-designed part. In the determination of the similarity, the shape similarity between the parts can be determined according to the design feature parameters. For example, the distance between the design feature parameters of the to-be-designed part and each skin part in the library can be compared to determine the shape similarity.

[0040] The determination of the similarity can include the determination of the surface similarity, the inner hole similarity and the recessed area similarity. The surface similarity, the inner hole similarity and the recessed area similarity are integrated by a weighted average method to obtain the similarity between the parts, and then the similar skin part of the to-be-designed part is determined.

[0041] Step 130, extracting the design knowledge and design rules of the similar skin part in the aircraft skin simulation die face design knowledge base.

[0042] Figure 2 It is a schematic diagram of an aircraft skin simulation die face design knowledge base provided by an embodiment of the present application. As shown in Figure 2 The aircraft skin simulation die face design knowledge base can include a skin part simulation die face design scheme library, a material library and a rule library. The scheme library can include design schemes of all skin part simulation die faces. The design scheme can include product models, process design information, die face design systems, simulation data, mold design, part stretch forming feature parameters, part knowledge, etc. The material library mainly includes all related material information of skin stretch forming. The rule library can be general design rules of stretch forming.

[0043] Extracting the design knowledge and design rules of the similar skin part in the knowledge base can specifically be obtaining the design scheme, material and general knowledge corresponding to the similar skin part.

[0044] Step 140, driving design of the to-be-designed part according to the design knowledge and design rules to obtain a target design part.

[0045] Figure 3 It is a driving design flowchart of a skin part provided by an embodiment of the present application. As shown in Figure 3 The flow-driven design includes stretch coordinate system driving design, hole filling driving design, boundary filling driving design, boundary extension driving design and mold face driving design. After the similar skin part is determined, the to-be-designed skin part can be driven designed according to the design knowledge and design rules of the similar skin part to obtain a target design part.

[0046] On the basis of the above-mentioned embodiments, optionally, after driving design is performed on the to-be-designed part according to the design knowledge and the design rules to obtain the target design part, the method further includes: sending the target design part to a part design detection platform, and obtaining a detection result of the target design part by the part design detection platform; when the detection result is a detection pass, adding the feature parameters of the target design part, the design knowledge and the design rules to the aircraft skin simulation die surface design knowledge base; when the detection result is a detection fail, obtaining a design rule adjustment parameter transmitted by the part design detection platform; updating the design rules and the target design part by using the design rule adjustment parameter, and adding the feature parameters of the target design part, the design knowledge and the design rules to the aircraft skin simulation die surface design knowledge base.

[0047] The part design detection platform can detect the target design part to determine whether the target design part meets the design requirements. The part design detection platform can be a man-machine interactive detection platform or an automatic detection platform. When the part design detection platform is an automatic detection platform, the part design detection platform can detect whether the surface of the target design part meets the fairness.

[0048] For example, the detection method of the fairness of the surface can be: intercepting the part in the offset planes of the front view plane (i.e., the xoy plane in the coordinate system xyz), the side view plane (i.e., the xoz plane in the coordinate system xyz) and the top view plane (i.e., the yoz plane in the coordinate system xyz) in the coordinate system of the target design part to obtain the surface cross-section line. Discretizing the surface cross-section line to obtain the surface reference points. Dividing the difference between the curvatures of adjacent surface reference points by the distance between the adjacent surface reference points to obtain a ratio. If the ratio is greater than a preset threshold, it is determined that the surface does not meet the fairness, and the adjacent surface reference points are reported. If the ratios corresponding to all adjacent surface reference points are less than or equal to the preset threshold, it is determined that the surface meets the fairness.

[0049] When the part design detection platform is a man-machine interactive detection platform, a designer can judge the target design part to determine whether the target design part meets the design requirements.

[0050] When the target design part passes the detection, the feature parameters of the target design part, the design knowledge and the design rules can be added to the aircraft skin simulation die surface design knowledge base to enrich the knowledge base and realize the automatic design of more skin parts.

[0051] When the target design part fails the inspection, the adjustments made by the designer to the part can be obtained through the part design inspection platform, that is, the design rule adjustment parameters can be obtained. For example, the stretching coefficient of the similar skin part is 100. When the target design part is obtained by the stretching system for the designed skin part, the target design part fails the inspection. The designer indicates that the stretching coefficient of the target design part should be 109, and 109 / 100 is used as the design rule adjustment parameter. That is, the target design part is stretched by 109 / 100. The design rule is adjusted to 109 / 100×100, that is, when the subsequent matching target design part is driven by the similar skin part for design, its stretching coefficient is 109, not 100.

[0052] The technical solution of this embodiment obtains the part to be designed and extracts the design feature parameters of the part to be designed; the design feature parameters include: curved surfaces, inner holes and recessed areas; obtains an aircraft skin simulation mold surface design knowledge base, and determines similar skin parts of the part to be designed in the aircraft skin simulation mold surface design knowledge base according to the design feature parameters; extracts design knowledge and design rules of similar skin parts in the aircraft skin simulation mold surface design knowledge base; drives the design part according to the design knowledge and design rules to obtain the target design part, thereby solving the problem of driven design of aircraft skin parts, and can perform driven design of the mold surface of new skin parts based on the design knowledge and design rules of completed skin parts, and can automatically perform skin part design to reduce the manpower required for design.

[0053] Example 2

[0054] Figure 4 This is a flow chart of a method for driving the design of an aircraft skin simulation mold surface according to the second embodiment of the present invention. This embodiment is a further refinement of the above technical solution. The technical solution in this embodiment can be combined with various optional solutions in one or more of the above embodiments. Figure 4 As shown, the method includes:

[0055] Step 210: Obtain the part to be designed and extract the design feature parameters of the part to be designed.

[0056] The design feature parameters include: curved surface, inner hole and concave area.

[0057] In an optional implementation of the embodiment of the present application, the design feature parameters of the part to be designed are extracted, including: establishing a coordinate system according to the part to be designed, and determining a part containing box under the coordinate system; dividing a grid area in the front view plane of the coordinate system, and selecting a first preset number of curved surface reference points in each grid area; in each grid area, determining the barycentric coordinates under the part containing box according to the selected curved surface reference points, and calculating the curvatures of the projection points of the barycentric coordinates on the part to be designed; generating a reference plane according to each curved surface reference point, and calculating the normal vector of the reference plane in each grid area; taking the barycentric coordinates, the normal vector and the curvatures in each grid area as the curved surface design feature parameters of the part to be designed.

[0058] The established coordinate system can be a mold coordinate system established according to a mold used in part design. The mold coordinate system can be a three-dimensional coordinate system xyz. The front view plane can be the xoy plane in the coordinate system xyz. The grid area division on the xoy plane can be performed along the horizontal direction and the vertical direction, for example, the grid area can be divided into 10x10 grid areas.

[0059] For each grid area, a barycentric coordinate and a reference plane can be determined. The generated reference plane can be a data expression form. The barycentric coordinates, the normal vector and the curvatures can be obtained by mathematical methods, and the embodiment of the present application does not make specific limitations thereto.

[0060] In an optional implementation of the embodiment of the present application, the design feature parameters of the part to be designed are extracted, including: determining the inner boundary of the part to be designed through topological relationship, and calculating the inner boundary barycenter and the average radius of the inner boundary from the inner boundary barycenter; taking the inner boundary barycenter and the average radius as the inner hole center and the inner hole radius of the inner hole design feature parameter in the design feature parameters, respectively.

[0061] In an optional implementation of the embodiment of the present application, the design feature parameters of the part to be designed are extracted, including: establishing a coordinate system according to the part to be designed, and determining a part containing box in the coordinate system; in the coordinate system, intersecting an equidistant offset plane parallel to the side view plane with the part to be designed to obtain a second preset number of section lines; discretizing each section line into section reference points, and traversing from one end in each section line, taking three continuous section reference points each time, and moving to the other end; the first and second section reference points in the current traversal form a first reference vector, and the second and third section reference points form a second reference vector; according to the trend of the section line, the positive and negative of the first reference vector and the second reference vector are determined, and the recessed area corresponding to the change of the positive and negative is determined; when the recessed area of the current section line overlaps with the recessed area of the last section line, the overlapping recessed areas are merged, and the recessed center and the recessed radius of each recessed area are determined; the recessed center and the recessed radius of each recessed area are taken as the recessed area design feature parameters of the part to be designed.

[0062] The side view plane can be the xoz plane in the coordinate system xyz. The plane parallel to the xoz plane and intersecting the part to be designed for section cutting is called the offset plane of the xoz plane. The line intersecting the offset plane and the part to be designed is the section line. In the embodiment of the present application, it is assumed that the recessed area is circular. Half of the maximum length of the same recessed area is the recessed radius. The midpoint of the same recessed area is the recessed center.

[0063] Step 220, acquiring the aircraft skin simulation die surface design knowledge base, and determining the similar skin part of the part to be designed in the aircraft skin simulation die surface design knowledge base according to the design feature parameters.

[0064] In an optional implementation of the embodiment of the present application, the similar skin part of the part to be designed is determined in the aircraft skin simulation die surface design knowledge base according to the design feature parameters, including: according to the curved surface design feature parameters of the part to be designed, determining the distance of the gravity center coordinates, the deviation angle of the normal vector and the curvature difference of the corresponding positions of each skin part in the aircraft skin simulation die surface design knowledge base; according to the distance of the gravity center coordinates, the deviation angle of the normal vector and the curvature difference of the part to be designed and the skin part, determining the optimal target and the worst target, and forming a comparison feature vector; according to the distance of the comparison feature vector, determining the curved surface similarity of the part to be designed and the skin part.

[0065] In the process of calculating the center of gravity coordinate distance, the normal vector deviation angle and the curvature difference value of each position between the part to be designed and the skin part in the knowledge base, each data can be arranged in the order of position to form a corresponding feature vector. For example, the center of gravity coordinate distance feature vector a, the normal vector deviation angle feature vector b and the curvature difference value feature vector c can be generated. The similarity calculation can be performed by the Technique for Order Preference by Similarity to Ideal Solution (TOPSIS).

[0066] Taking the center of gravity coordinate distance feature vector a as an example, the normalization processing can be performed on each feature vector first to obtain a'=(a max -a) / (a max -a min ), a max is the maximum center of gravity coordinate distance value corresponding to each grid area of all parts, and a min is the minimum center of gravity coordinate distance value corresponding to each grid area of all parts. In all grid areas, the optimal target A + =(1,...) and the worst target A - =(0,...) can be selected to form a comparison feature vector. The distance D + =|A + -a'| of each normalized center of gravity coordinate distance feature vector to the optimal target and the distance D - =|A - -a'| to the worst target are calculated. The center of gravity similarity in the surface similarity can be determined as TSim=∑Sim / n. Wherein, Sim=D - / (D + +D - ), and n is the number of grid areas. The similarity calculation process of the normal vector deviation angle and the curvature difference value is similar to that of the center of gravity coordinate distance, which will not be repeated here.

[0067] After obtaining the similarity of the center of gravity coordinate distance, the normal vector deviation angle and the curvature difference value, the weight of each similarity can be assigned. The surface similarity can be obtained according to the weighted average value of the similarity of the center of gravity coordinate distance, the normal vector deviation angle and the curvature difference value.

[0068] In an optional implementation of the embodiment of the present application, the similar skin part of the part to be designed is determined in the aircraft skin simulation die face design knowledge base according to the design feature parameters, comprising: obtaining all the hole radii of the part to be designed and the skin parts in the aircraft skin simulation die face design knowledge base, and determining the minimum hole radius; determining the hole penalty value according to each hole radius and the minimum hole radius, and determining the hole similarity of the part to be designed and the skin part according to the hole penalty value.

[0069] wherein the minimum hole radius is d min , the hole radius of the part to be designed is r, and the hole radius corresponding to the skin part is r1. The hole penalty value of the part to be designed is F=(a*d min +b*|r-r1|) / (a+b). Wherein a and b are adjustment parameters. The hole similarity is Tsim=1-∑F / n. n is the number of holes.

[0070] In an optional implementation of the embodiment of the present application, the similar skin part of the part to be designed is determined in the aircraft skin simulation die face design knowledge base according to the design feature parameters, comprising: obtaining all the hole radii of the part to be designed and the skin parts in the aircraft skin simulation die face design knowledge base, and determining the minimum hole radius; determining the hole penalty value according to each hole radius and the minimum hole radius, and determining the hole similarity of the part to be designed and the skin part according to the hole penalty value.

[0071] Wherein the determination method of the recess region similarity is the same as the determination method of the hole similarity, which is to calculate the penalty value according to the radius, and to determine the similarity according to the penalty value. Here, it is not repeated.

[0072] Step 230, extracting the design knowledge and design rules of the similar skin part in the aircraft skin simulation die face design knowledge base.

[0073] Step 240, driving the design of the part to be designed according to the design knowledge and design rules to obtain the target design part.

[0074] Step 250, sending the target design part to the part design detection platform and obtaining the detection result of the target design part by the part design detection platform.

[0075] Step 260, when the detection result is passed, adding the feature parameters, design knowledge and design rules of the target design part to the aircraft skin simulation die face design knowledge base.

[0076] Step 270, when the detection result is not passed, obtaining the design rule adjustment parameters transmitted by the part design detection platform.

[0077] Step 280, the design rule adjustment parameter is used to update the design rule and the target design part, and the feature parameters, the design knowledge and the design rule of the target design part are added to the aircraft skin simulation surface design knowledge base.

[0078] The technical scheme of the embodiment is characterized in that: the design feature parameters of the to-be-designed part are acquired and extracted; the design feature parameters include: a curved surface, an inner hole and a recessed area; the aircraft skin simulation surface design knowledge base is acquired, and the similar skin part of the to-be-designed part is determined in the aircraft skin simulation surface design knowledge base according to the design feature parameters; the design knowledge and the design rule of the similar skin part are extracted in the aircraft skin simulation surface design knowledge base; the to-be-designed part is driven to be designed according to the design knowledge and the design rule, and the target design part is obtained; the target design part is sent to the part design detection platform, and the detection result of the target design part by the part design detection platform is acquired; when the detection result is passed, the feature parameters, the design knowledge and the design rule of the target design part are added to the aircraft skin simulation surface design knowledge base; when the detection result is failed, the design rule adjustment parameter transmitted by the part design detection platform is acquired; the design rule and the target design part are updated by using the design rule adjustment parameter, and the feature parameters, the design knowledge and the design rule of the target design part are added to the aircraft skin simulation surface design knowledge base, thereby solving the problem of driving design of the aircraft skin part, enabling the driving design of the new skin part surface based on the design knowledge and the design rule of the completed skin part, automatically designing the skin part and reducing the manpower required for design.

[0079] Embodiment three

[0080] Figure 5 It is a structural schematic diagram of an aircraft skin simulation surface driving design device provided according to the embodiment three of the application. As shown in the figure, Figure 5 The device comprises: a design feature parameter extraction module 510, a similar skin part determination module 520, a design knowledge extraction module 530 and a driving design module 540.

[0081] Among them:

[0082] The design feature parameter extraction module 510 is used to acquire the to-be-designed part and extract the design feature parameters of the to-be-designed part; the design feature parameters include: a curved surface, an inner hole and a recessed area;

[0083] The similar skin part determination module 520 is used to acquire the aircraft skin simulation surface design knowledge base, and determine the similar skin part of the to-be-designed part in the aircraft skin simulation surface design knowledge base according to the design feature parameters;

[0084] The design knowledge extraction module 530 is configured to extract design knowledge and design rules of similar skin parts from the aircraft skin simulation surface design knowledge base.

[0085] The driving design module 540 is configured to drive design of the to-be-designed part according to the design knowledge and the design rules, to obtain a target design part.

[0086] Optionally, the apparatus further comprises:

[0087] The detection result acquisition module is configured to, after driving design of the to-be-designed part according to the design knowledge and the design rules, to obtain the target design part, send the target design part to a part design detection platform, and acquire a detection result of the target design part by the part design detection platform;

[0088] The first knowledge base updating module is configured to, when the detection result is a detection pass, add the feature parameters of the target design part, the design knowledge and the design rules to the aircraft skin simulation surface design knowledge base;

[0089] The adjustment parameter acquisition module is configured to, when the detection result is a detection fail, acquire a design rule adjustment parameter transmitted by the part design detection platform;

[0090] The second knowledge base updating module is configured to update the design rules and the target design part by using the design rule adjustment parameter, and add the feature parameters of the target design part, the design knowledge and the design rules to the aircraft skin simulation surface design knowledge base.

[0091] Optionally, the design feature parameter extraction module 510 comprises:

[0092] The part bounding box determination unit is configured to establish a coordinate system according to the to-be-designed part, and determine a part bounding box in the coordinate system;

[0093] The curved surface reference point determination unit is configured to divide a grid-shaped region in an orthographic plane in the coordinate system, and select a first preset number of curved surface reference points in each grid-shaped region;

[0094] The curvature determination unit is configured to, in each grid-shaped region, determine a barycentric coordinate in the part bounding box according to the selected curved surface reference points, and calculate a curvature of a projection point of the barycentric coordinate on the to-be-designed part in each grid-shaped region;

[0095] The normal vector determination unit is configured to generate a reference plane by fitting according to the curved surface reference points, and calculate a normal vector of the reference plane in each grid-shaped region;

[0096] The curved surface design feature parameter determination unit is configured to take the barycentric coordinate, the normal vector and the curvature in each grid-shaped region as the curved surface design feature parameters of the to-be-designed part.

[0097] Optionally, the design feature parameter extraction module 510 comprises:

[0098] an average radius determination unit configured to determine the inner boundary of the part to be designed according to the topological relationship, and calculate the center of gravity of the inner boundary and the average radius of the inner boundary from the center of gravity of the inner boundary;

[0099] an inner hole design feature parameter determination unit configured to take the center of gravity of the inner boundary and the average radius as the inner hole center and the inner hole radius of the inner hole design feature parameter in the design feature parameter, respectively.

[0100] Optionally, the design feature parameter extraction module 510 comprises:

[0101] a part containing box determination unit configured to establish a coordinate system according to the part to be designed, and determine the part containing box in the coordinate system;

[0102] a cross-section line determination unit configured to intersect the equidistant offset plane parallel to the side view plane with the part to be designed in the coordinate system to obtain a second preset number of cross-section lines;

[0103] a cross-section reference point determination unit configured to discretize each cross-section line into a cross-section reference point, and traverse each cross-section line from one end, taking three continuous cross-section reference points each time and moving to the other end;

[0104] a reference vector determination unit configured to form a first reference vector from the first and second cross-section reference points in the current traversal, and form a second reference vector from the second and third cross-section reference points;

[0105] a recessed area determination unit configured to determine the positive and negative of the first reference vector and the second reference vector according to the direction of the cross-section line, and determine the recessed area corresponding to the change of the positive and negative;

[0106] a recessed radius determination unit configured to merge the overlapping recessed areas when the recessed area of the current cross-section line overlaps the recessed area of the previous cross-section line, and determine the recessed center and the recessed radius of each recessed area;

[0107] a recessed area design feature parameter determination unit configured to take the recessed center and the recessed radius of each recessed area as the recessed area design feature parameter of the part to be designed.

[0108] Optionally, the similar skin part determination module 520 comprises:

[0109] a curved surface deviation information determination unit configured to determine the distance of the center of gravity, the deviation angle of the normal vector and the curvature difference of the corresponding position of each skin part in the aircraft skin simulation surface design knowledge base according to the curved surface design feature parameter of the part to be designed;

[0110] The comparative feature vector determination unit is configured to determine optimal target and worst target according to the distance between the center of gravity coordinates of the part to be designed and the skin part, the normal vector deviation angle and the curvature difference value, and form a comparative feature vector.

[0111] The curved surface similarity determination unit is configured to determine the curved surface similarity of the part to be designed and the skin part according to the distance of the comparative feature vector.

[0112] Optionally, the similar skin part determination module 520 comprises:

[0113] The minimum inner hole radius determination unit is configured to obtain all inner hole radii of the part to be designed and the skin part in the aircraft skin simulation surface design knowledge base, and determine the minimum inner hole radius.

[0114] The inner hole similarity determination unit is configured to determine the inner hole penalty value according to each inner hole radius and the minimum inner hole radius, and determine the inner hole similarity of the part to be designed and the skin part according to the inner hole penalty value.

[0115] Optionally, the similar skin part determination module 520 comprises:

[0116] The minimum recess radius determination unit is configured to obtain all recess radii of the part to be designed and the skin part in the aircraft skin simulation surface design knowledge base, and determine the minimum recess radius.

[0117] The recess region similarity determination unit is configured to determine the recess penalty value according to each recess radius and the minimum recess radius, and determine the recess region similarity of the part to be designed and the skin part according to the recess penalty value.

[0118] The driving design device of the aircraft skin simulation surface provided in the embodiments of the present application can execute the driving design method of the aircraft skin simulation surface provided in any embodiment of the present application, and has the corresponding function modules and beneficial effects of the execution method.

[0119] Embodiment four

[0120] Figure 6 A structural schematic diagram of an electronic device 10 that can be used to implement embodiments of the present application is shown. The electronic device is intended to represent various forms of digital computers, such as laptops, desktops, tablets, personal digital assistants, servers, blade servers, mainframes, and other appropriate computers. The electronic device can also represent various forms of mobile devices, such as personal digital assistants, cellular telephones, smartphones, wearable devices (e.g., headsets, glasses, watches, etc.), and other similar computing devices. The components shown here, their connections and relationships, and their functions, are meant to be examples only, and are not intended to limit the implementations of the applications described and / or claimed in this document.

[0121] like Figure 6 As shown, the electronic device 10 includes at least one processor 11 and a memory, such as a read-only memory (ROM) 12, a random access memory (RAM) 13, etc., which is communicatively connected to the at least one processor 11. The memory stores a computer program that can be executed by the at least one processor. The processor 11 can perform various appropriate actions and processes according to the computer program stored in the read-only memory (ROM) 12 or the computer program loaded from the storage unit 18 into the random access memory (RAM) 13. Various programs and data required for the operation of the electronic device 10 can also be stored in the RAM 13. The processor 11, ROM 12, and RAM 13 are connected to each other via a bus 14. An input / output (I / O) interface 15 is also connected to the bus 14.

[0122] Multiple components in the electronic device 10 are connected to the I / O interface 15, including an input unit 16, such as a keyboard, a mouse, etc.; an output unit 17, such as various types of displays, speakers, etc.; a storage unit 18, such as a magnetic disk, an optical disk, etc.; and a communication unit 19, such as a network card, a modem, a wireless communication transceiver, etc. The communication unit 19 allows the electronic device 10 to exchange information / data with other devices via a computer network such as the Internet and / or various telecommunication networks.

[0123] The processor 11 can be any general-purpose and / or specialized processing component with processing and computing capabilities. Some examples of the processor 11 include, but are not limited to, a central processing unit (CPU), a graphics processing unit (GPU), various specialized artificial intelligence (AI) computing chips, various processors running machine learning model algorithms, a digital signal processor (DSP), and any other suitable processor, controller, microcontroller, etc. The processor 11 executes the various methods and processes described above, such as the drive design method for the aircraft skin simulation mold surface.

[0124] In some embodiments, the method for driving the design of the aircraft skin simulation mold surface can be implemented as a computer program, which is tangibly contained in a computer-readable storage medium, such as the storage unit 18. In some embodiments, part or all of the computer program can be loaded and / or installed on the electronic device 10 via the ROM 12 and / or the communication unit 19. When the computer program is loaded into the RAM 13 and executed by the processor 11, one or more steps of the method for driving the design of the aircraft skin simulation mold surface described above can be performed. Alternatively, in other embodiments, the processor 11 can be configured to execute the method for driving the design of the aircraft skin simulation mold surface by any other appropriate means (for example, by means of firmware).

[0125] The various embodiments of the systems and techniques described above can be implemented in digital electronic circuitry, integrated circuitry, a field programmable gate array (FPGA), an application specific integrated circuit (ASIC), a system on a chip (SOC), a load programmable logic device (CPLD), computer hardware, firmware, software, and / or combinations thereof. These various embodiments can include implementation in one or more computer programs that are executable and / or interpretable on a programmable system including at least one programmable processor, which can be special or general purpose, coupled to receive data and instructions from, and to transmit data and instructions to, a storage system, at least one input device, and at least one output device.

[0126] Computer programs used to implement the processes of the application can be written in any combination of one or more programming languages. These computer programs can be provided to a processor of a general purpose computer, special purpose computer, or other programmable data processing apparatus, such that the computer program

[0127] In the context of the present application, a computer-readable storage medium can be a tangible medium that can contain or store computer programs for use by or in connection with an instruction execution system, apparatus, or device. Computer-readable storage media can include, but are not limited to, electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any suitable combination of the foregoing. Alternatively, a computer-readable storage medium can be a machine-readable signal medium. More specific examples of the machine-readable storage medium will include one or more lines of a program of instructions in a transitory signal, a portable computer diskette, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or Flash memory), an optical fiber, a portable compact disc read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing.

[0128] To provide for interaction with a user, the systems and techniques described here can be implemented on an electronic device having a display device (e.g., a CRT (cathode ray tube) or LCD (liquid crystal display) monitor) for displaying information to the user and a keyboard and a pointing device (e.g., a mouse or a trackball) by which the user can provide input to the electronic device. Other kinds of devices can be used to provide for interaction with a user as well; for example, feedback provided to the user can be any form of sensory feedback (e.g., visual feedback, auditory feedback, or tactile feedback); and input from the user can be received in any form, including acoustic, speech, or tactile input.

[0129] The systems and techniques described here can be implemented in a computing system that includes a back end component (e.g., as a data server), or that includes a middleware component (e.g., an application server), or that includes a front end component (e.g., a user computer having a graphical user interface or a Web browser through which a user can interact with an implementation of the systems and techniques described here), or any combination of such back end, middleware, or front end components. The components of the system can be interconnected by any form or medium of digital data communication (e.g., a communication network). Examples of communication networks include a local area network (LAN), a wide area network (WAN), a blockchain network, and the Internet.

[0130] The computing system can include clients and servers. A client and server are generally remote from each other and typically interact through a communication network. The relationship of client and server arises by virtue of computer programs running on the respective computers and having a client-server relationship to each other. A server can be a cloud server, also known as a cloud computing server or cloud host, which is a host product in the cloud computing service system, to solve the defects of large management difficulty and weak business scalability in traditional physical host and VPS service.

[0131] It should be understood that the various forms of flow shown above can be re-ordered, added to, or deleted from without departing from the scope of the present disclosure. For example, the steps recited in the present disclosure can be executed in parallel, executed in sequence, or executed in a different order, as long as the desired results of the present disclosure are achieved, and the present disclosure is not limited herein.

[0132] The specific embodiments described above are not intended to be limiting, and persons skilled in the art will appreciate that various modifications, combinations, sub-combinations and alternatives can be made to the specific embodiments without departing from the spirit and principles of the disclosure. Accordingly, the disclosure is not limited to the specific embodiments described above, but only by the scope of the appended claims.

Claims

1. A drive design method for aircraft skin simulation mold surface, characterized in that: include: Obtaining a part to be designed and extracting design feature parameters of the part to be designed; described Design feature parameters, including curved surfaces, inner holes, and recessed areas; Acquiring an aircraft skin simulation die surface design knowledge base, and determining a similar skin part of the part to be designed in the aircraft skin simulation die surface design knowledge base according to the design feature parameters; Extracting the design knowledge and design rules of the similar skin parts from the aircraft skin simulation die surface design knowledge base; The part to be designed is driven by design according to the design knowledge and design rules to obtain a target design part.

2. The method according to claim 1, characterized in that After the drive design of the part to be designed is performed according to the design knowledge and design rules to obtain the target design part, the method further includes: Sending the target design part to a part design testing platform, and obtaining a test result of the part design testing platform on the target design part; When the detection result is that the detection passes, the characteristic parameters, design knowledge and design rules of the target design part are added to the aircraft skin simulation die surface design knowledge base; When the detection result is failure, obtaining the design rule adjustment parameters transmitted by the part design detection platform; The design rule adjustment parameters are used to update the design rules and target design parts, and the characteristic parameters, design knowledge and design rules of the target design parts are added to the aircraft skin simulation die surface design knowledge base.

3. The method according to claim 1, characterized in that Extracting the design feature parameters of the part to be designed includes: Establishing a coordinate system according to the part to be designed, and determining the part containing box in the coordinate system; Dividing the front view plane in the coordinate system into grid-like regions, and selecting a first preset number of curved surface reference points in each grid-like region; In each grid-shaped area, the coordinates of the center of gravity under the part enclosing box are determined according to the selected surface reference points, and the curvature of the projection point of the center of gravity coordinate on the part to be designed in each grid-shaped area is calculated; Generate a reference plane by fitting the reference points on each surface, and calculate the normal vector of the reference plane in each grid area; The center of gravity coordinates, normal vectors and curvatures in each grid area are used as surface design feature parameters of the part to be designed.

4. The method according to claim 1, wherein Extracting the design feature parameters of the part to be designed includes: Determine the inner boundary of the part to be designed through topological relationships, and calculate the center of gravity of the inner boundary and the average radius of the inner boundary from the center of gravity of the inner boundary; The inner boundary center of gravity and the average radius are respectively used as the inner hole center and inner hole radius of the inner hole design feature parameters in the design feature parameters.

5. The method according to claim 1, wherein Extracting the design feature parameters of the part to be designed includes: Establishing a coordinate system according to the part to be designed, and determining the part containing box in the coordinate system; In the coordinate system, intersecting an equidistant offset plane parallel to the side view plane with the part to be designed to obtain a second preset number of cross-sectional lines; Discretize each section line into section reference points, and traverse each section line from one end, taking three consecutive section reference points each time and moving toward the other end; The first and second cross-section reference points in the current traversal constitute a first reference vector, and the second and third cross-section reference points constitute a second reference vector; Determine the positive and negative signs of the first reference vector and the second reference vector according to the direction of the cross-sectional line, and determine the concave area corresponding to the change in the positive and negative signs; When the concave area of ​​the current section line overlaps with the concave area of ​​the previous section line, the overlapping concave areas are merged, and the concave center and concave radius of each concave area are determined; The concave center and concave radius of each concave area are used as design feature parameters of the concave area of ​​the part to be designed.

6. The method according to claim 3, characterized in that Determining similar skin parts of the part to be designed in the aircraft skin simulation die surface design knowledge base according to the design feature parameters includes: Determine, based on the surface design feature parameters of the part to be designed, the centroid coordinate distance, normal vector deviation angle, and curvature difference of the corresponding position of each skin part in the aircraft skin simulation mold surface design knowledge base; Determine the optimal target and the worst target based on the center of gravity coordinate distance, normal vector deviation angle, and curvature difference between the part to be designed and the skin part, and form a comparative feature vector; The surface similarity between the part to be designed and the skin part is determined based on the distance between the compared eigenvectors.

7. The method according to claim 4, characterized in that Determining similar skin parts of the part to be designed in the aircraft skin simulation die surface design knowledge base according to the design feature parameters includes: Obtaining all inner hole radii of the part to be designed and the skin parts in the aircraft skin simulation die surface design knowledge base, and determining the minimum inner hole radius; Each inner hole penalty value is determined according to each inner hole radius and the minimum inner hole radius, and the inner hole similarity between the part to be designed and the skin part is determined according to each inner hole penalty value.

8. The method according to claim 5, characterized in that Determining similar skin parts of the part to be designed in the aircraft skin simulation die surface design knowledge base according to the design feature parameters includes: Obtaining all the concave radii of the part to be designed and the skin parts in the aircraft skin simulation die surface design knowledge base, and determining the minimum concave radius; Determine each concave penalty value according to each concave radius and the minimum concave radius, and determine the similarity of the concave area between the part to be designed and the skin part according to each concave penalty value.

9. An electronic device, characterized in that: The electronic device comprises: at least one processor; and a memory communicatively connected to the at least one processor; wherein, The memory stores a computer program executable by the at least one processor, and the computer program is executed by the at least one processor to enable the at least one processor to execute the method for driving design of an aircraft skin simulation mold surface according to any one of claims 1 to 8.

10. A computer-readable storage medium, characterized in that The computer-readable storage medium stores computer instructions, and the computer instructions are used to enable a processor to implement the driven design method for the aircraft skin simulation mold surface according to any one of claims 1 to 8 when executed.

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