A method and system for three-dimensional routing optimization of solar wing circuits

Abstract

The present application relates to the technical field of three-dimensional modeling optimization, and particularly relates to a solar wing circuit three-dimensional laying optimization method and system. The method comprises the following steps: obtaining a solar wing substrate model sub-block and constructing a corresponding ten sets of solar wing substrate cloth model; obtaining solar wing substrate geometric shape parameters, circuit element parameters and cloth constraint conditions and performing cloth position deduction and laying cloth sorting screening to generate a solar wing optimal laying cloth model; obtaining installation coordinates and wiring ports of corresponding electronic devices of diodes, connectors, supports and threading holes and performing cable wiring path planning to generate a solar wing circuit device cable wiring path; obtaining corresponding electronic device equipment wiring node table according to the installation coordinates and wiring ports of the electronic devices and designing output corresponding solar wing circuit wiring laying two-dimensional diagram, and also exporting corresponding solar wing circuit cable entity information. The present application can realize efficient design and accurate implementation of solar wing circuit three-dimensional laying.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of three-dimensional modeling optimization, and particularly relates to a solar wing circuit three-dimensional laying optimization method and system. BACKGROUND

[0002] With the continuous progress of spacecraft and satellite technology, solar energy has been widely used as the main energy supply method for spacecraft. As an important component of spacecraft, the solar wing undertakes the key task of converting solar energy into electrical energy. In recent years, three-dimensional circuit design has gradually become a research hotspot. By introducing three-dimensional modeling and multi-physical field simulation, researchers can more comprehensively evaluate the efficiency, power loss, temperature distribution, and other factors of circuit layout, further optimizing the circuit layout. In addition, the traditional solar wing circuit laying method usually adopts two-dimensional plane design, which optimizes the circuit layout on the surface of the battery panel to achieve efficient energy transmission. However, this design method does not fully consider the three-dimensional spatial characteristics of the solar wing, ignores the arrangement and interconnection of the circuit in the three-dimensional limited space, resulting in redundancy, congestion or unreasonable situations in circuit laying, thereby reducing the accuracy and efficiency of circuit optimization. SUMMARY

[0003] Therefore, it is necessary to provide a solar wing circuit three-dimensional laying optimization method and system to solve at least one of the above technical problems.

[0004] To achieve the above purpose, a solar wing circuit three-dimensional laying optimization method comprises the following steps:

[0005] Step S1: obtaining a solar wing substrate model sub-block, and constructing ten corresponding solar wing substrate layout models according to the solar wing substrate model sub-block;

[0006] Step S2: obtaining solar wing substrate geometric shape parameters, circuit element parameters, and layout constraint conditions, and performing layout position deduction on the corresponding solar wing substrate layout model based on the solar wing substrate geometric shape parameters, circuit element parameters, and layout constraint conditions to generate a corresponding solar wing layout position coordinate set; performing laying layout sorting and screening on the corresponding solar wing substrate layout model based on the solar wing layout position coordinate set to generate a solar wing optimal laying layout model;

[0007] Step S3: obtaining installation coordinates and wiring ports of diodes, connectors, supports, and threading holes corresponding to electronic devices, and combining the solar wing optimal laying layout model corresponding to the layout scheme to perform cable layout path planning on the installation coordinates and wiring ports of the diodes, connectors, supports, and threading holes corresponding to the electronic devices, to generate a solar wing circuit device cable routing path;

[0008] Step S4: Obtain the corresponding electronic device wiring node table according to the mounting coordinates of the diode, connector, bracket and wire hole corresponding electronic device and the wiring port, and generate the corresponding solar wing circuit three-dimensional optimization entity model based on the electronic device wiring node table combined with the solar wing circuit device cable routing path modeling; output the corresponding solar wing circuit wiring laying two-dimensional drawing from the solar wing circuit three-dimensional optimization entity model wiring design, and export the corresponding solar wing circuit cable entity information.

[0009] Further, step S1 includes the following steps:

[0010] Step S11: Obtain a solar wing substrate model sub-block;

[0011] Step S12: According to the arrangement of each solar wing substrate model sub-block along the lateral direction of the substrate, fill the entire string of circuit elements first in the center, and then judge whether the remaining area can be S-symmetrically laid according to the area, wherein the remaining area laying direction is from the center edge to both sides, to generate a corresponding lateral center priority symmetrically laid model of the solar wing substrate; similarly, fill the entire string from both sides to the center along the lateral direction of the substrate, and judge whether the remaining area can be S-symmetrically laid according to the area, wherein the remaining area laying direction is from both sides to the center, to generate a corresponding lateral two-side-to-center laying model of the solar wing substrate; similarly, fill the entire string from the center axis to both sides along the lateral direction of the substrate, and judge whether the remaining area can be S-symmetrically laid according to the area, wherein the remaining area laying direction is from the center to both sides, to generate a corresponding lateral center axis to both sides laying model of the solar wing substrate;

[0012] Step S13: Transpose the corresponding laying model in step S12 from the lateral direction of the substrate to the longitudinal direction to generate three sets of longitudinal transposed laying models corresponding to the solar wing substrate;

[0013] Step S14: According to the arrangement of each solar wing substrate model sub-block along the lateral direction of the substrate, cut the substrate into middle row area, two side row area and forbidden laying area at the preset compression point, lay the entire string in one direction from the leftmost side in the middle row area and the two side row area, supplement the flying piece in the forbidden laying area, and judge whether the remaining area on the right side can continue to be S-laid according to the area, to generate a corresponding lateral regionally laid model of the solar wing substrate; transpose the lateral regionally laid model from the lateral direction of the substrate to the longitudinal direction to generate a corresponding longitudinal transposed regionally laid model of the solar wing substrate;

[0014] Step S15: Take the lateral regionally laid model as a blueprint to optimize the middle row area to lay the entire string in one direction preferentially, and take the maximum laying as the highest priority, to generate a corresponding lateral regionally optimized laying model of the solar wing substrate; transpose the lateral regionally optimized laying model from the lateral direction of the substrate to the longitudinal direction to generate a corresponding longitudinal transposed optimized laying model of the solar wing substrate.

[0015] Further, the step S2 comprises the following steps:

[0016] Step S21: Obtain the solar wing substrate geometric shape parameters, including the length, width and thickness corresponding to the solar wing substrate;

[0017] Step S22: Obtain the circuit element parameters, including the size, shape and number corresponding to the circuit element;

[0018] Step S23: Obtain the cloth constraint conditions corresponding to the solar wing substrate, including the forbidden cloth area constraints and whether the S-shaped cloth constraint is satisfied corresponding to the above ten sets of cloth models;

[0019] Step S24: Based on the solar wing substrate geometric shape parameters, the circuit element parameters and the cloth constraint conditions, the corresponding solar wing substrate cloth model is deduced to generate the corresponding solar wing cloth position coordinate set;

[0020] Step S25: Based on the solar wing cloth position coordinate set, the corresponding solar wing substrate cloth model is laid and the cloth is sorted and screened to generate the solar wing optimal laid cloth model.

[0021] Further, the step S24 comprises the following steps:

[0022] Step S241: Based on the cloth constraint conditions, the corresponding solar wing substrate cloth model is analyzed to obtain the corresponding solar wing substrate forbidden cloth area space limitation relationship;

[0023] Step S242: Based on the solar wing substrate geometric shape parameters and the circuit element parameters, and combining the corresponding solar wing substrate forbidden cloth area space limitation relationship, the available geometry is planned to adjust the cloth arrangement position between the matching circuit element corresponding size and number and the available area on the substrate by using the heuristic search method, and the corresponding solar wing substrate available cloth position layout diagram is generated;

[0024] Step S243: Based on the S-shaped cloth constraint corresponding to the cloth constraint condition, the corresponding solar wing substrate available cloth position layout diagram is locally optimized to adjust the local position corresponding to the cloth based on the S-shaped cloth constraint and the minimum rotation angle, and the corresponding solar wing substrate cloth optimized layout diagram is generated;

[0025] Step S244: Based on the solar wing substrate cloth optimized layout diagram, the corresponding solar wing substrate cloth model is deduced to generate the corresponding solar wing cloth position coordinate set.

[0026] Further, the step S244 comprises the following steps:

[0027] A corresponding solar wing substrate layout coordinate system is established through the solar wing substrate patch optimization layout diagram;

[0028] Each patch in the solar wing substrate patch optimization layout diagram is subjected to geometric transformation derivation calculation based on the solar wing substrate layout coordinate system, so as to calculate the center coordinates, angles and relative position points of each patch in each solar wing substrate diagram;

[0029] The corresponding solar wing patch model is subjected to patch position deduction based on the center coordinates, angles and relative position points of each patch in each solar wing substrate diagram, so as to generate a corresponding solar wing patch position coordinate set.

[0030] Further, step S25 includes the following steps:

[0031] Step S251: calculate the corresponding solar wing patch effective area according to the solar wing patch position coordinate set;

[0032] Step S252: obtain the total area of the solar wing substrate, and calculate the patch rate corresponding to each solar wing patch model based on the ratio between the solar wing patch effective area and the total area of the solar wing substrate;

[0033] Step S253: based on the patch rate corresponding to each solar wing patch model, the corresponding solar wing substrate patch model is subjected to patch laying sorting and screening, sorted in descending order, and the solar wing patch model with the largest patch rate is selected as the optimal model to generate the solar wing optimal patch laying model.

[0034] Further, step S3 includes the following steps:

[0035] Step S31: obtain the installation coordinates of the corresponding electronic devices of the diode, connector, support and threading hole;

[0036] Step S32: obtain the wiring port of the corresponding electronic devices of the diode, connector, support and threading hole;

[0037] Step S33: create a three-dimensional device model according to the installation coordinates and wiring port of the corresponding electronic devices of the diode, connector, support and threading hole, to generate a solar wing circuit device three-dimensional model;

[0038] Step S34: through the combination of the patch scheme corresponding to the solar wing optimal patch laying model, the solar wing circuit device three-dimensional model is subjected to cable wiring path planning, to generate a solar wing circuit device cable routing path.

[0039] Further, step S34 includes the following steps:

[0040] The solar wing circuit device three-dimensional model is connected through the solar wing optimal laying patch model corresponding patch scheme to obtain a solar wing circuit device patch port connection skeleton model;

[0041] The circuit performance, electromagnetic compatibility and spatial layout constraints between the diodes, connectors, supports and threading holes corresponding electronic devices are obtained;

[0042] The cable wiring path planning between the devices based on the circuit performance, electromagnetic compatibility and spatial layout constraints between the diodes, connectors, supports and threading holes corresponding electronic devices is performed on the solar wing circuit device patch port connection skeleton model to generate a solar wing circuit device cable wiring path.

[0043] Further, the step S4 comprises the following steps:

[0044] Step S41: performing electrical logic connection analysis according to the installation coordinates and connection ports of the diodes, connectors, supports and threading holes corresponding electronic devices to generate corresponding device electrical connection relationships between the electronic devices;

[0045] Step S42: generating corresponding electronic device device connection node tables based on the corresponding device electrical connection relationships between the electronic devices and combining the installation coordinates and connection port connections of the diodes, connectors, supports and threading holes corresponding electronic devices;

[0046] Step S43: generating corresponding solar wing circuit three-dimensional optimization entity models based on the electronic device device connection node tables and combining solar wing circuit device cable wiring path modeling;

[0047] Step S44: outputting corresponding solar wing circuit wiring laying two-dimensional diagrams through solar wing circuit three-dimensional optimization entity model wiring design and exporting corresponding solar wing circuit cable entity information, including corresponding patch models, types, starting and ending connection ports, cable lengths and cable quality information.

[0048] Further, the present application also provides a solar wing circuit three-dimensional laying optimization system for performing the solar wing circuit three-dimensional laying optimization method as described above, and the solar wing circuit three-dimensional laying optimization system comprises:

[0049] A solar wing patch modeling module is used to obtain a solar wing substrate and construct ten sets of solar wing substrate patch models according to the solar wing substrate;

[0050] The substrate laying cloth screening module is used for acquiring solar wing substrate geometric shape parameters, circuit element parameters and cloth constraint conditions, and performing cloth position deduction on the corresponding solar wing substrate cloth model based on the solar wing substrate geometric shape parameters, the circuit element parameters and the cloth constraint conditions, so as to generate a corresponding solar wing cloth position coordinate set; the solar wing substrate cloth model is subjected to laying cloth sorting screening based on the solar wing cloth position coordinate set, so as to generate a solar wing optimal laying cloth model;

[0051] The circuit device path planning module is used for acquiring installation coordinates and wiring ports of diodes, connectors, supports and wire holes corresponding to electronic devices, and performing cable wiring path planning on the installation coordinates and the wiring ports of the diodes, the connectors, the supports and the wire holes corresponding to the electronic devices in combination with a cloth scheme corresponding to the solar wing optimal laying cloth model, so as to generate a solar wing circuit device cable wiring path;

[0052] The three-dimensional entity wiring output module is used for acquiring an electronic device equipment wiring node table corresponding to the installation coordinates and the wiring ports of the diodes, the connectors, the supports and the wire holes, and generating a corresponding solar wing circuit three-dimensional optimization entity model based on the electronic device equipment wiring node table in combination with the solar wing circuit device cable wiring path modeling; the solar wing circuit three-dimensional optimization entity model wiring design outputs a corresponding solar wing circuit wiring laying two-dimensional graph, and exports corresponding solar wing circuit cable entity information.

[0053] The beneficial effects of the present application are as follows:

[0054] 1、The solar wing circuit three-dimensional laying optimization method provided by the application, compared with the prior art, has the beneficial effects that the advantages and disadvantages of different design schemes can be comprehensively evaluated at the early stage of design by obtaining a solar wing substrate model sub-block and considering the design and generation of ten sets of cloth piece models, data support is provided for optimizing and selecting the optimal cloth piece scheme, this multi-scheme design not only improves the flexibility of design, but also effectively reduces the cost of later adjustment and modification, provides beneficial guarantee for improving design efficiency and shortening the research and development period. Secondly, by obtaining the geometric shape parameters of the solar wing substrate, the circuit element parameters and the cloth piece constraint conditions, and based on these parameters, the cloth piece position deduction and sorting screening of the solar wing substrate cloth piece model are carried out, the core purpose of this process is to ensure the best configuration of the solar wing substrate cloth piece, through the accurate geometric shape and circuit element parameters, not only the stability and functionality of the overall design of the solar wing substrate can be ensured, but also the rationality of each cloth piece in structure can be ensured, the cloth piece position deduction and sorting screening process can avoid conflicts and resource waste in the design process, ensure that the cloth piece can ensure the maximum power output while avoiding redundant design, thereby optimizing the overall efficiency of the solar wing. At the same time, by screening out the optimal cloth piece model, clear guidance is provided for subsequent cloth laying and circuit layout, and the density of the cloth piece and the optimization degree of the layout can be further improved, achieving better overall structural performance, so that the three-dimensional space characteristics of the solar wing can be fully considered, and the redundancy, congestion or unreasonable situation of the circuit laying can be avoided. Then, by obtaining the installation coordinates and connection ports of the diode, connector, support and threading hole, and combining the optimal cloth piece model of the solar wing, the cable routing path planning is carried out, the core purpose of this process is to ensure the efficiency and reliability of the circuit system, while avoiding interference and resource waste between lines, through the path planning of the circuit device, the rationality of the cable routing can be ensured, so that each line can fully utilize the space of the solar wing, avoid excessive interweaving or unnecessary complex path, thereby reducing the risk of circuit failure, the path planning can also effectively avoid the line being too long or too short, ensure the stable transmission of current, and improve the reliability and efficiency of the system. At the same time, accurate path planning helps to improve the accuracy in the solar wing assembly process, reduce errors, improve production efficiency, and finally lay a foundation for the reliability and long-term use of the product, the optimization in this stage not only improves the performance of the circuit, but also further reduces the complexity and difficulty in the production process.Finally, by generating a 3D optimized model of the solar panel circuit based on the equipment wiring node table and cable routing path, the circuit system can be debugged and optimized more precisely, ensuring that the arrangement of electrical components meets design requirements. The 3D optimized solid model provides a visual design interface, allowing designers to conduct more intuitive evaluation and adjustments in a virtual environment, reducing errors and corrections caused by design problems in actual production. By exporting the physical information of the cables, precise cable specifications and layout requirements can be provided for actual manufacturing, avoiding mismatch problems that occur in on-site manufacturing. At the same time, the 2D diagram of the circuit wiring can provide clear operational guidance for subsequent assembly, installation, and debugging. This step fully considers the layout and interconnection of the circuit in a finite 3D space during the design process, which not only improves the electrical performance of the solar panel but also enhances the accuracy and efficiency of the solar panel circuit optimization effect.

[0055] 2. The solar panel circuit three-dimensional laying optimization system proposed in this invention is composed of a solar panel fabrication modeling module, a substrate laying and screening module, a circuit device path planning module, and a three-dimensional physical wiring output module. It can realize the arbitrary solar panel circuit three-dimensional laying optimization method described in this invention. It is used to combine the operations between the computer programs running on each module to realize the solar panel circuit three-dimensional laying optimization method. The internal structure of the system cooperates with each other, which can greatly reduce repetitive work and manpower input, and can quickly and effectively provide a more accurate and efficient solar panel circuit three-dimensional laying optimization process, thereby simplifying the operation process of the solar panel circuit three-dimensional laying optimization system. Attached Figure Description

[0056] Other features, objects, and advantages of the invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0057] Figure 1 This is a schematic diagram of the steps in the three-dimensional laying optimization method for solar panel circuits of the present invention;

[0058] Figure 2 for Figure 1 A detailed flowchart of step S1;

[0059] Figure 3 for Figure 1 A detailed flowchart of step S2. Detailed Implementation

[0060] The technical method of the present application will be described clearly and completely below in conjunction with the drawings. Obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0061] In addition, the drawings are only schematic illustrations of the present application and are not necessarily drawn to scale. Identical reference numerals in the drawings represent identical or similar parts, and thus repeated descriptions thereof will be omitted. Some of the block diagrams shown in the drawings are functional entities, which do not necessarily have to correspond to physically or logically independent entities. The functional entities can be implemented in the form of software, or in one or more hardware modules or integrated circuits, or in different network and / or processor methods and / or microcontroller methods.

[0062] It should be understood that although the terms "first", "second" and the like can be used herein to describe various elements, these elements should not be limited by these terms. These terms are only used to distinguish one element from another. For example, without departing from the scope of the exemplary embodiments, a first element can be referred to as a second element, and similarly a second element can be referred to as a first element. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0063] To achieve the above-mentioned purpose, please refer to Figures 1 to 3 The present application provides a three-dimensional laying optimization method for solar wing circuit, which comprises the following steps:

[0064] Step S1: Obtain a solar wing substrate model sub-block, and construct ten corresponding solar wing substrate patch models according to the solar wing substrate model sub-block;

[0065] Step S2: Obtain the solar wing substrate geometric shape parameters, circuit element parameters and patch constraint conditions, and perform patch position deduction on the corresponding solar wing substrate patch model based on the solar wing substrate geometric shape parameters, circuit element parameters and patch constraint conditions, to generate a corresponding solar wing patch position coordinate set; perform laying patch sorting and screening on the corresponding solar wing substrate patch model based on the solar wing patch position coordinate set, to generate an optimal solar wing laying patch model;

[0066] Step S3: Obtain the installation coordinates and wiring ports of the electronic devices corresponding to the diodes, connectors, supports and wire holes, and combine the patch scheme corresponding to the optimal laying patch model of the solar wing to plan the cable routing path of the installation coordinates and wiring ports of the electronic devices corresponding to the diodes, connectors, supports and wire holes, to generate the solar wing circuit device cable routing path;

[0067] Step S4: Obtain the corresponding electronic device wiring node table according to the installation coordinates and wiring ports of the electronic devices corresponding to the diodes, connectors, supports and wire holes, and generate the corresponding solar wing circuit three-dimensional optimization entity model based on the electronic device wiring node table and the solar wing circuit device cable routing path modeling; output the corresponding solar wing circuit wiring laying two-dimensional graph from the solar wing circuit three-dimensional optimization entity model wiring design, and export the corresponding solar wing circuit cable entity information.

[0068] In the embodiment of the present application, please refer to Figure 1 As shown in the step flow diagram of the solar wing circuit three-dimensional laying optimization method of the present application, in the present example, the solar wing circuit three-dimensional laying optimization method comprises the following steps:

[0069] Step S1: Obtain the solar wing substrate model sub-block, and construct ten sets of solar wing substrate patch models according to the solar wing substrate model sub-block;

[0070] In the embodiment of the present application, by opening the overall design file of the solar wing in computer-aided design (CAD) software, using the model segmentation function thereof, the solar wing substrate model is segmented into multiple sub-blocks according to the substrate structure characteristics and circuit laying requirements, for example, for a rectangular solar wing substrate with a size of 2500 mm long, 1200 mm wide and 5 mm thick, the substrate is segmented into 10 model sub-blocks according to the functional areas and size ratios, numbered from SB-01 to SB-10, and the vertex coordinates, size and other geometric information of each sub-block are accurately recorded in the CAD model database. Based on these sub-blocks, ten sets of solar wing substrate layout models are constructed in the layout design module of the CAD software through different layout strategies. When constructing the horizontal center priority symmetric layout model, a string of circuit elements composed of 10 elements with a size of 50 mm long and 30 mm wide are closely arranged in the center of the substrate with a width of 600 mm and a length covering the full length, and then the remaining area is calculated to determine whether it can be laid out symmetrically in S shape, and if the condition is met, the layout is performed from the center edge to both sides. When constructing the horizontal two-side-to-center layout model, the remaining area in the center is processed after the string of elements is laid out from both sides of the substrate to the center. When constructing the horizontal middle axis-to-two-side layout model, the string of elements is laid out from the middle axis to both sides and the remaining areas on both sides are processed. The three horizontal layout models are converted to longitudinal direction through the rotation function, and three sets of longitudinal layout models are obtained. In addition, there are horizontal regional layout models and their longitudinal converted versions, horizontal regional optimized layout models and their longitudinal converted versions, which are all constructed according to specific rules. All the models are saved in.Part format and named according to the layout strategy.

[0071] Step S2: Obtain the solar wing substrate geometric shape parameters, circuit element parameters and layout constraint conditions, and perform layout position deduction on the corresponding solar wing substrate layout model based on the solar wing substrate geometric shape parameters, circuit element parameters and layout constraint conditions to generate a corresponding set of solar wing layout position coordinates; perform laying layout sorting screening on the corresponding solar wing substrate layout model based on the solar wing layout position coordinate set to generate an optimal solar wing laying layout model;

[0072] In the embodiment of the present application, the geometric shape parameters of the solar wing substrate are obtained through the attribute query function of the CAD software and recorded in "Solar Wing Substrate Geometric Parameter Table.xlsx", such as the substrate length of 2500 mm, the width of 1200 mm, and the thickness of 5 mm. The circuit element parameters, including size, shape and quantity, are obtained from the circuit element model library by using the database management function of the CAD software, and sorted into "Circuit Element Parameter Summary Table.xlsx", for example, 50 cuboid circuit elements with a length of 30 mm, a width of 20 mm, and a height of 5 mm. In the CAD software, for ten sets of cloth piece models, the cloth piece constraint conditions are set by using the annotation and marking functions, such as the forbidden cloth area range, and whether the S-shaped cloth piece constraint is met is judged by combining the CAD secondary development interface with the Python script. Based on the above data, the cloth piece position is deduced by using Python combined with the Shapely library. Taking the horizontally central priority symmetrical cloth piece model as an example, the clothable area is determined according to the substrate size and the forbidden cloth area, the elements are arranged in the clothable area according to the element size and quantity, the element position is adjusted by using the heuristic search algorithm to ensure that the constraint condition is not violated, and the left lower corner vertex coordinates of each element are recorded to form a cloth piece position coordinate set. The above operation is repeated for the remaining nine sets of cloth piece models to obtain ten coordinate sets. Then, by using the Pymoo library of Python, based on the non-dominated sorting genetic algorithm NSGA-II, the cloth piece models are sorted in descending order of cloth piece rate by taking the cloth piece compactness and the circuit connection length as optimization objectives, and the horizontal division area optimization cloth piece model with the largest cloth piece rate is selected as the optimal cloth piece laying model of the solar wing.

[0073] Step S3: Obtain the installation coordinates and wiring ports of the corresponding electronic devices of the diodes, connectors, supports and threading holes, and plan the cable wiring path of the installation coordinates and wiring ports of the corresponding electronic devices of the diodes, connectors, supports and threading holes in combination with the cloth piece scheme corresponding to the optimal cloth piece laying model of the solar wing, to generate the cable wiring path of the solar wing circuit device.

[0074] In the embodiment of the present application, by obtaining the cloth scheme corresponding to the optimal cloth laying model of the solar wing in the CAD software, the installation coordinates and connection port information of the corresponding electronic devices of the diode, connector, support and threading hole are obtained, in the cable routing design module of the software, the cable routing path planning is carried out for the electronic devices in combination with the cloth scheme corresponding to the optimal cloth laying model of the solar wing, the cable path is planned from the connection port of the diode, the cable path creation tool is used to plan the cable direction, for example, when the path from the P1 port of the diode D-01 to the P2 port of the connector CON-001 is planned, the wiring needs to avoid the substrate forbidden area and other electronic devices, and the requirement that the minimum bending radius is 5 times the cable diameter is met, the path is planned along the wiring channel reserved in the cloth scheme, and the software collision detection function is used to check whether the path interferes with other devices in real time, if there is interference, the path is adjusted, and after the cable path planning between all electronic devices is completed, the solar wing circuit device cable routing path is finally generated.

[0075] Step S4: Obtain the corresponding electronic device wiring node table according to the installation coordinates and connection port of the corresponding electronic devices of the diode, connector, support and threading hole, and generate the corresponding solar wing circuit three-dimensional optimization entity model based on the electronic device wiring node table and the solar wing circuit device cable routing path modeling; output the corresponding solar wing circuit wiring laying two-dimensional drawing from the solar wing circuit three-dimensional optimization entity model wiring design, and export the corresponding solar wing circuit cable entity information.

[0076] In the embodiment of the present application, by using Python combined with pandas library, the electrical logic connection analysis is carried out according to the functions and design requirements of the electronic devices, a table containing all electrical connection relationships of the electronic devices is generated, the table is integrated with the installation coordinate table and the connection port table data to generate the electronic device wiring node table, and in the CAD software, the three-dimensional model of the electronic device is accurately assembled by using the assembly design module, such as moving the diode D-01 model to the (300, 400) position and moving the connector CON-001 model to the (500, 600) position, then creating the cable three-dimensional model according to the cable routing path and accurately connecting the device connection port to generate the solar wing circuit three-dimensional optimization entity model, saving as “.Product” file, finally, the three-dimensional model is projected and converted into a two-dimensional drawing by using the software engineering drawing module, setting the scale of 1:10 and labeling the size information, and using the attribute extraction function to export the cable entity information, including the corresponding cloth model, model, starting and ending connection port, cable length and cable quality information, which are arranged into a table and output as “Solar wing circuit wiring laying drawing and cable information.dwg” and “Solar wing circuit cable entity information table.xlsx” files, providing technical data for production and manufacturing. Figure 1 The same as saving as “Solar wing circuit wiring laying drawing and cable information.dwg” and “Solar wing circuit cable entity information table.xlsx” files, providing technical data for production and manufacturing.

[0077] Furthermore, step S1 includes the following steps:

[0078] Step S11: Obtain the solar panel substrate model sub-block;

[0079] Step S12: Arrange the sub-blocks of each solar panel substrate model along the horizontal direction of the substrate. First, fill the center with a whole string of circuit elements. Then, calculate the area of ​​the remaining area to determine whether S-shaped symmetrical arrangement is possible. The arrangement direction of the remaining area is from the center edge to both sides to generate the horizontal center-priority symmetrical arrangement model of the solar panel substrate. Similarly, fill the whole string of elements from both sides to the center along the horizontal direction of the substrate. Determine whether S-shaped symmetrical arrangement is possible in the remaining area of ​​the center based on the area. The arrangement direction of the remaining area is from both sides to the center to generate the horizontal two-sided to center arrangement model of the solar panel substrate. Similarly, fill the whole string of elements from the central axis to both sides along the horizontal direction of the substrate. Calculate the area of ​​the remaining areas on both sides to determine whether S-shaped symmetrical arrangement is possible. The arrangement direction of the remaining areas is from the center to both sides to generate the horizontal central axis to both sides arrangement model of the solar panel substrate.

[0080] Step S13: Transpose the corresponding fabric pattern in step S12 along the horizontal direction of the substrate to the vertical direction for fabric pattern deduction and arrangement, so as to generate three sets of vertically transposed fabric patterns corresponding to the solar panel substrate.

[0081] Step S14: Arrange the sub-blocks of each solar panel substrate model along the horizontal direction of the substrate. Cut the substrate into a middle row area, two side rows area and a no-lay row area using the preset clamping point. Arrange the middle row area and two side rows in a single direction starting from the leftmost side. Add flying pieces to the no-lay row area. Calculate whether the remaining area on the right can continue to be arranged in an S-shape according to the area to generate the horizontal sub-regional layout model corresponding to the solar panel substrate. Transpose the horizontal sub-regional layout model along the horizontal direction of the substrate to the vertical direction to generate the vertically transposed sub-regional layout model corresponding to the solar panel substrate.

[0082] Step S15: Optimize the horizontally divided area layout model as a blueprint, prioritize the unidirectional part in the middle row area, and take the largest layout as the highest priority to generate the horizontally divided area optimized layout model corresponding to the solar panel substrate; transpose the horizontal direction of the substrate in the horizontally divided area optimized layout model to the vertical direction to generate the vertically transposed optimized layout model corresponding to the solar panel substrate.

[0083] As an embodiment of the present invention, reference Figure 2 As shown, Figure 1 A detailed flowchart of step S1 is shown below. In this embodiment, step S1 includes the following steps:

[0084] Step S11: Obtain the solar panel substrate model sub-block;

[0085] In the embodiment of the present application, by opening the overall design file of the solar wing through computer aided design (CAD) software in the three-dimensional laying optimization process of the solar wing circuit, the solar wing substrate model is accurately segmented into multiple sub-blocks according to the structural characteristics of the solar wing substrate and the circuit laying requirements by using the model segmentation function of the CAD software. Assuming that the solar wing substrate is a rectangular structure with a size of 2000 mm in length and 1000 mm in width, it is segmented into 10 model sub-blocks with different sizes according to the functional areas and size ratios, numbered from SB-01 to SB-10. The geometric size and shape information of each sub-block is stored in the model database of the CAD software. For example, the SB-01 sub-block is a rectangle with a length of 500 mm and a width of 300 mm, and its vertex coordinates are (0, 0, 0), (500, 0, 0), (500, 300, 0), and (0, 300, 0). These data provide basic model information for subsequent sheet laying operations.

[0086] Step S12: According to the arrangement of each solar wing substrate model sub-block along the lateral direction of the substrate, the whole string of circuit elements is first laid in the center, and then the remaining area is calculated to determine whether S-type symmetric sheet laying can be performed. The sheet laying direction of the remaining area is from the center edge to both sides. A corresponding lateral center priority symmetric sheet laying model of the solar wing substrate is generated. Similarly, the whole string is laid from both sides to the center along the lateral direction of the substrate, and the remaining area in the center is calculated to determine whether S-type symmetric sheet laying can be performed. The sheet laying direction of the remaining area is from both sides to the center. A corresponding lateral two-side-to-center sheet laying model of the solar wing substrate is generated. Similarly, the whole string is laid from the center axis to both sides along the lateral direction of the substrate, and the remaining area on both sides is calculated to determine whether S-type symmetric sheet laying can be performed. The sheet laying direction of the remaining area is from the center to both sides. A corresponding lateral center axis to both sides sheet laying model of the solar wing substrate is generated.

[0087] In the embodiment of the present application, the previously obtained solar wing substrate model sub-blocks are arranged in the layout design module of the CAD software according to the lateral direction of the substrate (assuming along the width direction of the substrate). Taking a certain model of solar wing substrate as an example, the whole string of circuit elements is first laid in the center region. Assuming that the whole string of circuit elements consists of 10 identical elements, each element has a size of 50 mm in length and 30 mm in width, and is closely arranged in the region with a center width of 600 mm and a length covering the full length of the substrate. The elements are placed from the center to both sides in turn until the region is filled with the whole string of elements. Then, the area of the remaining region is calculated to determine whether S-type symmetric sheet laying can be performed. If the remaining region has a width of 200 mm and a length of 2000 mm, the total area is 400000 mm 2 , and the minimum area required for a single S-type sheet laying is 5000 mm 2, and the calculated area can accommodate 80 S-shaped cloth pieces, and the symmetry condition is met, then the S-shaped cloth pieces are arranged from the center edge to both sides to generate a horizontal center priority symmetric cloth piece model corresponding to the solar wing substrate. Similarly, when arranging the horizontal two-side-to-center cloth pieces, the entire string of circuit elements is arranged from both sides of the substrate to the center, and then the remaining area in the center is determined whether it can be arranged in an S-shaped symmetric manner according to the above area calculation method. If the condition is met, the cloth pieces are arranged from both sides to the center, thereby generating a horizontal two-side-to-center cloth piece model. In the horizontal center axis-to-both-side cloth piece operation, the entire string of elements is arranged from the center axis to both sides, and then the remaining area on both sides is determined whether it can be arranged in an S-shaped symmetric manner according to the area calculation method. If the condition is met, the cloth pieces are arranged from the center to both sides, and finally a horizontal center axis-to-both-side cloth piece model is generated.

[0088] Step S13: The cloth piece model corresponding to the step S12 is transposed from the horizontal direction of the substrate to the vertical direction to generate three sets of vertical transposed cloth piece models corresponding to the solar wing substrate.

[0089] In the embodiment of the present application, the three horizontal cloth piece models generated in step S12 are transposed from the horizontal direction of the substrate to the vertical direction (assuming the length direction of the substrate) in the transformation operation module of the CAD software through rotation and mirroring functions. Taking the horizontal center priority symmetric cloth piece model as an example, the entire cloth piece model is selected and rotated 90 degrees using the rotation tool to change the original horizontal cloth piece direction to the vertical direction. Then, the size and position of the model are adjusted to ensure that the element layout meets the vertical cloth piece requirements. Repeat this operation to transpose the horizontal two-side-to-center cloth piece model and the horizontal center axis-to-both-side cloth piece model in the same way to generate corresponding vertical transposed cloth piece models, a total of three sets of vertical transposed cloth piece models, which provide a basis for subsequent comparison and analysis of the effects of different cloth piece arrangements in the vertical direction.

[0090] Step S14: According to the arrangement of each solar wing substrate model sub-block in the horizontal direction of the substrate, the substrate is cut at the preset compression point as the middle row area, the two side row areas, and the forbidden cloth row area. The middle row area and the two side row areas are unidirectionally clothed from the leftmost side, the forbidden cloth row area is supplemented with flying pieces, and the right side remaining area is calculated according to the area to determine whether it can continue to be arranged in an S-shaped manner. To generate a horizontal regional cloth piece model corresponding to the solar wing substrate; and the horizontal regional cloth piece model is transposed from the horizontal direction of the substrate to the vertical direction to generate a vertical transposed regional cloth piece model corresponding to the solar wing substrate.

[0091] In the embodiment of the present application, by arranging the solar wing substrate model sub-blocks along the substrate transverse direction again, in the CAD software, according to the preset compression point position, the substrate is segmented into the middle row area, the two side row areas and the forbidden row area by using the cutting tool, assuming that the preset compression point divides the substrate transversely into three areas with a width ratio of 3:2:1, the middle row area has a width of 500 mm, the two side row areas each have a width of 300 mm, and the forbidden row area has a width of 200 mm, in the middle row area and the two side row areas, starting from the leftmost side, according to the element size and the circuit connection requirement, the whole string of circuit elements is arranged in one direction, assuming that the whole string of elements contains 15 elements, which are sequentially and closely arranged in the middle row area and the two side row areas, for the forbidden row area, a size-adapted flying piece is used for supplement to ensure the integrity of the circuit connection. Then, the area of the remaining area on the right side is calculated to determine whether the S-shaped piece can continue to be arranged, if the remaining area meets the piece arrangement condition, the S-shaped piece arrangement operation is performed, and finally the transverse divided area piece arrangement model corresponding to the solar wing substrate is generated. Then, by rotating the transverse divided area piece arrangement model in the CAD software, the model along the substrate transverse direction is transposed to the longitudinal direction, the size and position of the model are adjusted to adapt to the longitudinal layout, and finally the longitudinal transposed divided area piece arrangement model corresponding to the solar wing substrate is generated.

[0092] Step S15: taking the transverse divided area piece arrangement model as a blueprint for optimization to arrange the whole string of elements in one direction in the middle row area preferentially and to arrange the largest piece as the most preferential piece, and generating the transverse divided area optimized piece arrangement model corresponding to the solar wing substrate; transposing the transverse divided area optimized piece arrangement model along the substrate transverse direction to the longitudinal direction to generate the longitudinal transposed optimized piece arrangement model corresponding to the solar wing substrate.

[0093] In the embodiment of the present application, based on the transverse divided area piece arrangement model generated in step S14, further optimization is performed in the optimization design module of the CAD software, in the middle row area, the whole string arrangement operation in one direction is preferentially performed, and the largest piece is arranged as the most preferential piece, assuming that there are two pieces of different sizes, the sizes are 80 mm long and 60 mm wide and 50 mm long and 30 mm wide respectively, the piece with the size of 80 mm long and 60 mm wide is preferentially placed in the middle row area, and is sequentially arranged according to the circuit connection order to ensure that the piece is closely arranged and meets the circuit design requirement, after the optimized piece arrangement in the middle row area is completed, the piece arrangement in the two side row areas and the remaining area is adjusted according to the same optimization principle, and thus the transverse divided area optimized piece arrangement model corresponding to the solar wing substrate is generated. Finally, by rotating the transverse divided area optimized piece arrangement model in the CAD software, the model along the substrate transverse direction is transposed to the longitudinal direction, the size, position and element layout of the model are finely adjusted to meet the requirement of longitudinal laying, and finally the longitudinal transposed optimized piece arrangement model corresponding to the solar wing substrate is generated, which provides the final optimized piece arrangement scheme for the three-dimensional laying of the solar wing circuit.

[0094] Further, step S2 includes the following steps:

[0095] Step S21: Obtain the solar wing substrate geometric shape parameters, including the length, width and thickness corresponding to the solar wing substrate;

[0096] Step S22: Obtain the circuit element parameters, including the size, shape and number corresponding to the circuit element;

[0097] Step S23: Obtain the cloth constraint conditions corresponding to the solar wing substrate, including the forbidden cloth area constraint and whether the S-shaped cloth constraint is met corresponding to the above ten sets of cloth models;

[0098] Step S24: Based on the solar wing substrate geometric shape parameters, the circuit element parameters and the cloth constraint conditions, the corresponding solar wing substrate cloth model is deduced to generate the corresponding solar wing cloth position coordinate set;

[0099] Step S25: Based on the solar wing cloth position coordinate set, the corresponding solar wing substrate cloth model is laid and the cloth is sorted and screened to generate the optimal solar wing laid cloth model.

[0100] As an embodiment of the present application, referring to Figure 3 , it is Figure 1 the detailed step flowchart of step S2 in the embodiment, and step S2 in the embodiment includes the following steps:

[0101] Step S21: Obtain the solar wing substrate geometric shape parameters, including the length, width and thickness corresponding to the solar wing substrate;

[0102] In the embodiment of the present application, after completing the solar wing substrate model sub-block division and the generation of various cloth models, the solar wing substrate geometric shape parameters are obtained through the attribute query function of the CAD software, the solar wing overall design file is opened, the solar wing substrate model is selected in the model tree, the attribute viewing instruction is executed, and the software automatically extracts and displays the length, width and thickness parameters corresponding to the substrate. Assuming that the solar wing substrate is a regular rectangular structure, its length is 2500mm, its width is 1200mm, and its thickness is 5mm, which facilitates subsequent step calling and analysis, and provides substrate size basic data for cloth position deduction.

[0103] Step S22: Obtain the circuit element parameters, including the size, shape and number corresponding to the circuit element;

[0104] In the embodiment of the present application, the acquisition of the circuit element parameters also relies on the database management function of the CAD software. In the circuit element model library, different types of circuit element models are selected in sequence. Taking a certain type of circuit element as an example, the size of the selected circuit element is 30 mm long, 20 mm wide, and 5 mm high, and the shape is a cuboid. At the same time, the number of the circuit element of this type is 50 in the element list file. For other types of circuit elements, such as capacitors and diodes, the above operation is repeated. The size, shape, and quantity information of all circuit elements are sorted into the corresponding table. The table is divided into different worksheets according to the element type. Each worksheet records the element name, size (length, width, and height), shape description, quantity, and other information in detail, ensuring comprehensive and accurate acquisition of circuit element parameters and providing element data support for subsequent sheeting operations.

[0105] Step S23: Acquire the sheeting constraint conditions corresponding to the solar wing substrate, including the above ten sets of sheeting model corresponding forbidden area constraints and whether to meet the S-type sheeting constraint;

[0106] In the embodiment of the present application, by using the annotation and marking functions of the CAD software, the sheeting constraint conditions are set for the previously generated ten sets of solar wing substrate sheeting models (including three horizontal, three vertical, horizontal region division, vertical transposed region division, horizontal region division optimization, and vertical transposed optimization sheeting models). The forbidden area graph is drawn and the attribute label is added to clearly define the forbidden area constraints of each model. For example, in the horizontal center priority symmetrical sheeting model, the area with a substrate edge distance of 50 mm is marked as a forbidden area. In the vertical transposed region division sheeting model, the circular area with a radius of 30 mm around the compression point is set as a forbidden area. For whether to meet the S-type sheeting constraint, a Python script is written to judge through the secondary development interface of the CAD software. The script iterates through the remaining available area of each sheeting model, calculates the area and shape of the region, and compares it with the standard geometric requirements of the S-type sheeting. If the area is less than the minimum area required by a single S-type sheeting (assuming 5000 mm 2 ), it is determined that the S-type sheeting constraint is not met, and “No” is marked in the corresponding record line of the table. Otherwise, “Yes” is marked. The table records the forbidden area range and S-type sheeting constraint results of the ten sets of sheeting models one by one, providing constraint condition basis for subsequent sheeting position deduction.

[0107] Step S24: Based on the solar wing substrate geometric shape parameters, circuit element parameters, and sheeting constraint conditions, the corresponding solar wing substrate sheeting model is subjected to sheeting position deduction to generate a corresponding solar wing sheeting position coordinate set;

[0108] In the embodiment of the present application, by using Python programming language combined with open source geometric calculation library (such as Shapely) to deduce the layout position based on the obtained solar wing substrate geometric shape parameters, circuit element parameters and layout constraints, first, the corresponding solar wing substrate geometric shape parameters, circuit element parameters and layout constraints are read into the Python program, taking the horizontally central priority symmetrical layout model as an example, according to the substrate length of 2500 mm, width of 1200 mm and the layout forbidden area constraint (edge 50 mm is the layout forbidden area), the layout area is determined as a rectangle with a length of 2500 mm and a width of 1100 mm, for the circuit element, according to its size (such as circuit element with a length of 30 mm and a width of 20 mm) and quantity (50), arrangement attempt is carried out in the layout area, starting from the center, placing the elements in turn according to the layout rules, each time an element is placed, the position relationship between the element and the layout forbidden area and the placed elements is calculated through the Shapely library to ensure that the layout constraints are not violated, in the placement process, the left lower corner vertex coordinates of each element are recorded as the layout position coordinates, when all elements are placed, all layout position coordinates of the model are sorted into a list to form a solar wing layout position coordinate set, the above operation is repeated for the remaining nine layout models, and finally ten solar wing layout position coordinate sets corresponding to the ten layout models are obtained and stored in text files named after the model name.

[0109] Step S25: Based on the solar wing layout position coordinate set, the corresponding solar wing substrate layout model is subjected to laying and layout sorting screening to generate an optimal solar wing laying and layout model.

[0110] In the embodiment of the present application, after obtaining the ten sets of solar wing cloth position coordinates, a multi-objective optimization algorithm (such as the non-dominated sorting genetic algorithm NSGA-II) is used to sort and screen the corresponding solar wing substrate cloth model based on the Python Pymoo library, the set of cloth position coordinates is imported into the algorithm program as input data, and the optimization objectives are set to include the compactness of the cloth (the more compact the element layout is, the better), the length of the circuit connection (the shorter the connection line is, the better), the satisfaction degree of the S-shaped cloth (if the S-shaped cloth constraint is met, the score is increased), and the like. Taking the compactness of the cloth as an example, the ratio of the minimum circumscribed rectangle area of the region occupied by all elements to the area of the available cloth area is calculated, and the closer the ratio is to 1, the higher the compactness is. For the length of the circuit connection, the total length of the connection line is calculated according to the electrical connection relationship between the elements, and the shorter the length is, the higher the score is. The algorithm performs multiple rounds of iterative calculation and comparison on the ten sets of cloth models, sorts the cloth models according to the comprehensive scores of the optimization objectives, and after calculation and screening, the cloth model with the highest score is determined as the optimal solar wing laying cloth model. Assuming that the final horizontal area optimization cloth model performs best in the comprehensive evaluation of various indicators, the cloth position coordinates, element layout and other information of the model are sorted and output to the corresponding background file, which contains the model schematic diagram, coordinate data table, optimization index score details and other contents, thereby providing an accurate and reliable guidance scheme for the actual three-dimensional laying of the solar wing circuit.

[0111] Further, step S24 includes the following steps:

[0112] Step S241: based on the cloth constraint condition, the cloth space restriction analysis is performed on the corresponding solar wing substrate cloth model to obtain the corresponding solar wing substrate forbidden cloth region space restriction relationship.

[0113] In the embodiment of the present application, after completing the solar wing substrate cloth patch constraint condition setting, ten sets of solar wing substrate cloth patch models are analyzed for spatial restriction by using Python programming language combined with the secondary development interface of CAD software. Taking the horizontally centered priority symmetric cloth patch model as an example, the forbidden cloth area information of the model is read from the cloth constraint condition, the area with a distance of 50 mm from the edge of the substrate is the forbidden cloth area, the geometric boundary data of the substrate model is obtained through the API interface of the CAD software, the forbidden cloth area is modeled in the three-dimensional space, the polygon mesh data of the forbidden cloth area is generated, and the spatial topology analysis algorithm is used to calculate the position relationship between the forbidden cloth area and the overall space of the substrate. For example, by calculating the intersection and union of the forbidden cloth area polygon and the substrate boundary polygon, the specific range and shape of the forbidden cloth area on the substrate are determined, and these spatial restriction relationships are recorded in mathematical expressions and graphical ways, such as storing the forbidden cloth area polygon as a geometric object using the Shapely library, which contains the vertex coordinates, area, and distance from the substrate boundary of the forbidden cloth area polygon. The above operation is repeated for the remaining nine sets of cloth patch models, and finally the spatial restriction relationship of the solar wing substrate forbidden cloth area corresponding to the ten sets of models is obtained, which provides basic data for subsequent available area planning.

[0114] Step S242: Based on the solar wing substrate geometric shape parameters and the circuit element parameters, and combined with the corresponding solar wing substrate forbidden cloth area spatial restriction relationship, available geometry planning is performed to adjust the cloth arrangement position between the matching circuit element corresponding size and quantity and the available area on the substrate by using a heuristic search method, and a corresponding solar wing substrate available cloth position layout diagram is generated;

[0115] In the embodiment of the present application, by using the heuristic search algorithm library (such as NetworkX) of Python, the available geometry planning is carried out based on the acquired solar wing substrate geometric shape parameters, circuit element parameters and the spatial restriction relationship of the forbidden area obtained in step S241, taking the longitudinal transposition of the regional area layout model as an example, given that the substrate length is 2500 mm and the width is 1200 mm, and the forbidden area is a circular area with a radius of 30 mm around the compression point, first, according to the spatial restriction relationship of the forbidden area, the forbidden area is removed from the overall substrate space to obtain the available area, and the available area is polygonal modeled by using the Shapely library to divide it into multiple sub-areas, then, for the circuit elements (such as 50 circuit elements with a length of 30 mm and a width of 20 mm), a greedy algorithm is used to attempt to arrange the elements, starting from a corner of the available area, placing the elements in order according to the element size, and preferentially selecting sub-areas that can accommodate more elements, in the process of placing, a graph model of the element layout is constructed by using the NetworkX library, the nodes represent the elements, and the edges represent the positional relationship between the elements, ensuring that the elements do not overlap and meet the electrical connection requirements, and the placement position and order of the elements are constantly adjusted until all the elements are placed in the available area, generating a solar wing substrate available layout diagram of the layout position, and the layout diagram is saved in a two-dimensional vector graphics format (such as SVG), and the element position, available area boundary and forbidden area range are clearly marked in the diagram, providing an intuitive layout reference for subsequent layout position optimization.

[0116] Step S243: based on the corresponding S-shaped layout constraint within the layout constraint condition, the solar wing substrate available layout diagram of the corresponding layout position is locally optimized, the local position of the layout corresponding to the S-shaped layout constraint is adjusted based on the S-shaped layout constraint, and the solar wing substrate layout optimization layout diagram corresponding to the layout is generated;

[0117] In the embodiment of the present application, by using the previously generated solar wing substrate cloth available layout diagram, according to the S-shaped cloth constraint within the cloth constraint condition, using the Python graphics processing library (such as Pillow) and geometric calculation library (such as Shapely) to carry out local optimization of the cloth position, taking the transverse regional optimization of the available layout diagram of the cloth model as an example, the S-shaped cloth constraint judgment result of the model is obtained from the previous step, if the S-shaped cloth constraint is satisfied, the region in the layout diagram where the S-shaped cloth can be carried out is analyzed, the S-shaped cloth is abstracted into a specific geometric shape (such as a polygon surrounded by an S-shaped curve), the Shapely library is used to calculate the sub-region within the available region that meets the S-shaped cloth shape requirement, for the element layout in these sub-regions, the minimum rotation angle adjustment strategy is adopted, and by traversing the elements in the sub-region, the fitting degree of the element after rotating different angles (such as 0°, 90°, 180°, 270°) with the S-shaped cloth shape is calculated, and the rotation angle with the highest fitting degree is selected for adjustment. In the adjustment process, the electrical connection relationship between the elements is ensured to be unchanged and not to exceed the available region range, after the adjustment is completed, the cloth position layout diagram is updated, the solar wing substrate cloth optimization layout diagram is generated, and the optimized element position and S-shaped cloth layout effect are shown in the SVG format, which provides accurate layout scheme for the final cloth position deduction.

[0118] Step S244: based on the solar wing substrate cloth optimization layout diagram, the corresponding solar wing substrate cloth model is subjected to cloth position deduction to generate a corresponding solar wing cloth position coordinate set.

[0119] In the embodiment of the present application, based on the previously generated solar wing substrate cloth optimization layout diagram, the element position information in the layout diagram is converted into coordinate data using Python programming language, and the cloth position deduction is carried out, taking the cloth optimization layout diagram of the model on both sides of the transverse central axis as an example, the SVG parsing library (such as svg.path) is used to read the geometric figure information of the elements in the diagram, for each element figure, the coordinates of the lower left corner vertex in the substrate coordinate system are obtained, assuming that the left upper corner of the substrate is the coordinate origin (0, 0), the X axis is along the substrate width direction, and the Y axis is along the substrate length direction. By analyzing the SVG path data, the X and Y coordinate values of the lower left corner vertex of the element are calculated and recorded in a list. Repeat the above operation for all elements in the layout diagram, and arrange the obtained coordinate list into a standard coordinate set format, for example, for a layout diagram containing 100 elements, the generated coordinate set is [(x1, y1), (x2, y2), …, (x100, y100)], and the same operation is performed on the cloth optimization layout diagrams of the remaining nine cloth models. Finally, ten solar wing cloth position coordinate sets corresponding to ten cloth models are obtained, which provide accurate coordinate data support for subsequent selection of the optimal solar wing laying cloth model.

[0120] Further, step S244 includes the following steps:

[0121] A corresponding solar wing substrate layout coordinate system is established by the solar wing substrate layout optimization layout map;

[0122] In the embodiment of the present application, by taking the solar wing substrate layout optimization layout map corresponding to the transverse regional optimization layout model as an example, the svg.path library of Python is used to open the corresponding layout map, the top left corner vertex of the substrate is set as the origin of the solar wing substrate layout coordinate system, that is, the coordinates are (0, 0), the positive direction of the X axis is defined as extending rightward along the substrate width direction, the positive direction of the Y axis is defined as extending downward along the substrate length direction, the actual length and width dimensions of the substrate are obtained by analyzing the metadata and graphic attributes in the SVG file, it is assumed that the length of the substrate is 2500 mm and the width is 1200 mm, the scale range of the coordinate system is determined in this way, in the coordinate system, each unit length represents 1 mm, the definition information of the layout coordinate system is added to the Python program code in the form of comments, and the origin position of the coordinate system, the coordinate axis direction and the scale rule are recorded in detail in the generated auxiliary document, thereby providing a unified reference standard for subsequent geometric transformation and coordinate calculation.

[0123] Preferably, geometric transformation and derivation calculation are performed on each patch in the solar wing substrate layout optimization layout map based on the solar wing substrate layout coordinate system, so as to calculate the center coordinates, angles and relative position points of each patch in the solar wing substrate layout optimization layout map;

[0124] In the embodiment of the present application, by using the numpy library and the shapely library of Python to perform geometric transformation derivation calculation on each patch in the solar wing substrate layout optimization layout diagram based on the established solar wing substrate layout coordinate system, all patch graphics in the layout diagram are traversed, for each patch, the shapely library is used to abstract it into a geometric object such as a polygon or a rectangle, taking a rectangular patch with a length of 50 mm and a width of 30 mm as an example, the center coordinates are obtained by calculating the average value of the polygon vertex coordinates of the patch, assuming that the four vertex coordinates of the patch are (x1, y1), (x2, y1), (x2, y2), and (x1, y2), the center coordinates are ((x1+x2) / 2, (y1+y2) / 2), the angle is determined by calculating the angle between the edge of the patch and the positive direction of the X axis, if the edge vector of the patch is (x2-x1, y2-y1), the angle is calculated using the numpy.arctan2 function, that is, angle=numpy.arctan2(y2-y1, x2-x1), the radian value is converted to degree, for the relative position point, a vertex of the patch (such as the top left vertex) is selected as the reference point, the coordinates of the point relative to the origin of the coordinate system are calculated, and the relative position point coordinates are obtained, the center coordinates, angles and relative position point coordinates of each patch are recorded in a two-dimensional list, such as [[center_x1, center_y1, angle1, ref_x1, ref_y1], [center_x2, center_y2, angle2, ref_x2, ref_y2],...], forming the patch geometric information table of the layout diagram, which provides detailed data for patch position deduction.

[0125] Preferably, patch position deduction is performed on the corresponding solar wing substrate patch model based on the center coordinates, angles and relative position points of each patch in each solar wing substrate diagram to generate a corresponding solar wing patch position coordinate set.

[0126] In the embodiment of the present application, by deducing the cloth position of the corresponding solar wing substrate cloth model based on the previously obtained cloth geometry information table, the center coordinates, angles and relative position point coordinates of the cloth are used as input parameters to write a program using Python, the actual position of the cloth on the substrate is simulated by combining the overall structure and electrical connection requirements of the solar wing substrate cloth model, the cloth is rotated according to the angle information based on the center coordinates of the cloth as the reference, the rotation of the cloth is realized by using the matrix transformation function of the numpy library, for example, for a cloth with a center coordinate of (100, 100) and an angle of 30 degrees, the vertex coordinates of the cloth are transformed by constructing a rotation matrix to obtain the position of the rotated cloth, and then the cloth is accurately placed on the corresponding position of the substrate model according to the relative position point coordinates, the above operation is repeated for all cloths, the finally determined position coordinates of each cloth are recorded, and a standard coordinate set is arranged, assuming that the model has 80 cloths, the generated solar wing cloth position coordinate set is [(x1, y1), (x2, y2),..., (x80, y80)], and the optimization layout of the remaining nine sets of solar wing substrate cloth models is performed according to the same method and process, and finally ten solar wing cloth position coordinate sets corresponding to ten cloth models are obtained, which provides accurate position data support for subsequent selection of the optimal solar wing cloth laying model, and ensures the accuracy and feasibility of the cloth scheme in actual production and application.

[0127] Further, step S25 includes the following steps:

[0128] Step S251: calculating the corresponding solar wing cloth effective area according to the solar wing cloth position coordinate set;

[0129] In the embodiment of the present application, by using Python combined with shapely library to calculate the solar wing cloth effective area for the ten generated solar wing cloth position coordinate sets, taking the "horizontal regional optimization cloth model" as an example, the coordinate data in the file is read, and the coordinates of each cloth are converted into geometric objects in the shapely library, for example, for a rectangular cloth, a Polygon object is constructed according to the four vertex coordinates, assuming that there are 80 cloths in the model, the geometric objects of each cloth are traversed, and the area method of the shapely library is used to calculate the area of a single cloth, for example, the vertex coordinates of the cloth No. 1 are (10, 10), (60, 10), (60, 40) and (10, 40), after constructing the Polygon object, the area is calculated by the area method to be (60-10)×(40-10)=1500mm 2 The areas of all cloths are added to obtain the corresponding solar wing cloth effective area of the model, and the total area of the 80 cloths of the model is calculated to be 120000mm 2The same operation is performed on the remaining nine sets of solar wing panel position coordinates, and the panel effective area data corresponding to the ten panel models is obtained respectively.

[0130] Step S252: Obtain the total area of the solar wing substrate, and calculate the panel rate corresponding to each solar wing panel model based on the ratio between the solar wing panel effective area and the total area of the solar wing substrate.

[0131] In the embodiment of the present application, by obtaining the length and width parameters of the solar wing substrate from the previous step, assuming that the substrate length is 2500mm and the width is 1200mm, the total area of the solar wing substrate is calculated by the formula "area=length*width" as 2500*1200=3000000mm 2 A program is written using Python to read the panel effective area data of the ten panel models obtained in step S251 (stored in the corresponding files respectively), divide the panel effective area of each panel model by the total area of the solar wing substrate, and calculate the panel rate corresponding to each solar wing panel model. Taking the "lateral regional optimization panel model" as an example, the panel effective area is 120000mm 2 , then the panel rate is 120000÷3000000=0.04, i.e. 4%, and the panel rate result of each panel model is recorded in the corresponding table, which contains columns such as model name, panel effective area, total substrate area, and panel rate, for subsequent comparative analysis.

[0132] Step S253: Based on the panel rate corresponding to each solar wing panel model, the corresponding solar wing substrate panel model is sorted and screened, sorted in descending order, and the solar wing panel model with the largest panel rate is selected as the optimal model, and the optimal solar wing panel model is generated.

[0133] In the embodiment of the present application, by using the pandas library of Python to sort and screen the ten solar wing cloth model laying cloth based on the data in the previous table, after reading the table data, the sort_values function is used to sort the cloth model according to the cloth rate from large to small, assuming that the data order in the table before sorting is “horizontal center priority symmetric cloth model” “horizontal two side center cloth model” and the like, and the data order is adjusted to the model with the highest cloth rate after sorting, such as “horizontal regional optimization cloth model” “vertical transposition optimization cloth model” and the like, the solar wing cloth model with the highest cloth rate is screened out as the optimal model, after sorting, it is found that the cloth rate of “horizontal regional optimization cloth model” is the highest, which is 4%, and it is determined as the optimal solar wing laying cloth model, the related information of the optimal model, including the model name, cloth effective area, cloth rate and the like, is also attached with the cloth optimization layout of the model, cloth position coordinate set and the like, which provides the final optimization scheme for the three-dimensional laying of the solar wing circuit, and ensures that the cloth efficiency can be maximized in actual production, and the performance and reliability of the solar wing are improved.

[0134] Further, step S3 comprises the following steps:

[0135] Step S31: Obtain the installation coordinates of the diodes, connectors, supports and wire holes corresponding to the electronic devices;

[0136] In the embodiment of the present application, after the optimal solar wing laying cloth model is determined, the computer aided design (CAD) software is used to obtain the cloth position coordinate set and other related information from the previous step, and in the model tree of the CAD software, the solar wing substrate model is found, based on the established solar wing substrate layout coordinate system, the installation positions of the diodes, connectors, supports and wire holes corresponding to the electronic devices are accurately marked by using the measurement and marking functions of the software, taking the diode as an example, assuming that in the “horizontal regional optimization cloth model”, according to the cloth position coordinate set, the center coordinates of the installation position of the diode numbered D-01 are (300, 400), a mark point is created on the substrate model at the corresponding coordinate position by using the point creation tool of the CAD software, and the coordinate information of the point is recorded in the corresponding table, the first column of the table records the device name “diode D-01”, the second column and the third column record the X coordinate “300” and the Y coordinate “400” respectively, and the installation coordinates of the connectors, supports and wire holes and the like are obtained in the same way, and are recorded in the table, so that the installation positions of each device are accurately supported by the coordinate data for subsequent operation.

[0137] Step S32: Obtain the wiring ports of the diodes, connectors, supports and wire holes corresponding to the electronic devices;

[0138] In the embodiment of the present application, by continuing to use the CAD software, opening the relevant file containing the solar wing circuit design, finding the three-dimensional models of the diode, connector, bracket and threading hole in the electronic device model library, for each electronic device model, using the attribute editing function of the software, checking and recording the wiring port information, taking the connector as an example, selecting the connector model with the model number CON-001, finding the wiring port related attributes in the attribute window, which contains 4 wiring ports, marked as P1, P2, P3, P4 respectively, the shape of each port is circular, the diameter is 2mm, the coordinates of the port center relative to the center of the connector model are (5, 0, 0), (-5, 0, 0), (0, 5, 0), (0, -5, 0) respectively, these wiring port information is arranged in the corresponding table, the table is divided into different worksheets according to the device name, and the device model number, the number of wiring ports, the port number, the port shape, the size and the relative coordinates and other information are recorded in detail in each worksheet, and the same operation is performed on the diode, bracket and threading hole to ensure that the wiring port information of all electronic devices is obtained completely, and detailed data basis is provided for subsequent three-dimensional model creation and cable layout.

[0139] Step S33: creating a three-dimensional model of the device according to the installation coordinates and wiring ports of the corresponding electronic devices of the diode, connector, bracket and threading hole to generate a three-dimensional model of the solar wing circuit device;

[0140] In the embodiment of the present application, by using the three-dimensional modeling module in the CAD software, creating a three-dimensional model of the diode, connector, bracket and threading hole according to the data in the installation coordinate and wiring port corresponding table, taking the bracket as an example, according to its installation coordinates (500, 600), using the stretching modeling tool of the software, taking the design size of the bracket (100mm long, 80mm wide, 20mm high) as the parameter, creating a three-dimensional solid model of the bracket on the substrate model at the corresponding coordinate position, then according to the wiring port information of the bracket in the wiring port table, using the hole feature creation tool, creating a wiring hole with a diameter of 3mm on the bracket model at the corresponding position as the wiring port, and according to the same method, sequentially completing the three-dimensional model creation of the diode, connector and threading hole, and assembling all device models with the solar wing substrate model to ensure the relative position between the devices is accurate, finally generating a complete three-dimensional model of the solar wing circuit device, and saving it in the format of.Part, which contains detailed three-dimensional structure and accurate installation position information of all electronic devices.

[0141] Step S34: planning the cable layout path of the solar wing circuit device by combining the solar wing optimal laying piece model corresponding to the piece scheme to generate the solar wing circuit device cable layout path.

[0142] In the embodiment of the present application, by combining the patch scheme corresponding to the optimal patch laying model of the solar wing in the cable routing design module of the CAD software, the cable routing path of the solar wing circuit device three-dimensional model is planned, and based on the electrical connection requirement of the elements in the patch scheme, starting from one connection port of the diode, the cable path creation tool of the software is used to plan the cable direction in the three-dimensional space, considering that the forbidden area on the substrate, other electronic devices and the bending radius requirement of the routing process (assuming that the minimum bending radius is 5 times the diameter of the cable) are avoided, along the routing channel reserved in the patch scheme, the cable is gradually planned to pass through the connection port of the device such as the connector and the support, and finally reaches the connection port of the target device, in the planning process, the collision detection function of the software is used in real time to check whether the cable path interferes with other devices, if there is interference, the cable path is adjusted. For example, the cable path from the P1 port of the diode D-01 to the P2 port of the connector CON-001 is planned, a preliminary path is simulated in the three-dimensional model first, and the collision detection finds that there is interference with the support model, so the path is adjusted to bypass the support, and the detection is performed again until there is no interference, after the cable path of all electrical connections is planned, the solar wing circuit device cable routing path is generated, and saved in the format of.Product, the file records the starting point, end point, path shape and related parameter information of each cable in detail, providing accurate cable routing guidance scheme for the actual three-dimensional laying of the solar wing circuit.

[0143] Further, step S34 includes the following steps:

[0144] By combining the patch scheme corresponding to the optimal patch laying model of the solar wing, the patch port connection between each electronic device in the solar wing circuit device three-dimensional model is processed, and the patch port connection skeleton model between the solar wing circuit devices is obtained.

[0145] In the embodiment of the present application, by means of the CAD software, according to the cloth scheme corresponding to the optimal cloth laying model of the solar wing, the electrical connection relationship between each electronic device is determined, and by means of the wireframe modeling tool of the software, starting from the wiring ports of the electronic devices such as diodes, connectors, supports and threading holes, a cloth port wiring skeleton model is constructed, taking the diode numbered D-01 and the connector numbered CON-001 as examples, according to the cloth scheme, it is determined that there is an electrical connection between the two, in the three-dimensional model, a straight line segment is created from the center of the P1 wiring port of the diode D-01, and the straight line segment is extended to the center of the P2 wiring port of the connector CON-001, so as to represent the electrical connection line between the two, according to the same method, the wiring ports of all electronic devices having an electrical connection relationship are connected, in the connection process, the alignment and capture functions of the software are used to ensure that the line segment is accurately connected to the center position of the wiring port, after all the connections are completed, a cloth port wiring skeleton model between the solar wing circuit devices is generated, which intuitively presents the connection relationship between the devices in the form of a wireframe, and records the start point, end point coordinates and related attribute information of each connection line in detail.

[0146] Preferably, the circuit performance, electromagnetic compatibility and spatial layout constraints between the corresponding electronic devices of the diode, the connector, the support and the threading hole are obtained;

[0147] In the embodiment of the present application, by referring to the solar wing circuit design documents, electronic device technical manuals and relevant industry standards, the circuit performance, electromagnetic compatibility and spatial layout constraints between the corresponding electronic devices of the diode, the connector, the support and the threading hole are obtained, taking the circuit performance constraints as an example, the forward conduction voltage drop, maximum working current and other parameters of the diode are obtained from the electronic device technical manual, so as to determine the working requirements of the diode in the circuit; for the connector, the contact resistance, insulation resistance and other parameters are obtained, so as to ensure the reliability of the connection. In terms of electromagnetic compatibility, according to the relevant industry standards (such as GJB 151B-2013), the electromagnetic interference limitation requirements between the electronic devices are determined, including the radiation emission limit value, the conducted emission limit value and the like. For example, it is stipulated that the electromagnetic radiation intensity between adjacent electronic devices should not exceed a certain threshold value, so as to avoid mutual interference, and in terms of spatial layout constraints, according to the structural characteristics and cloth scheme of the solar wing substrate, the minimum spacing requirements between each electronic device are determined, such as stipulating that the distance between the connector and the support should not be less than 20 mm, so as to prevent mechanical interference between the devices. All the obtained constraint conditions are arranged into a corresponding table, which is classified according to the circuit performance, electromagnetic compatibility and spatial layout, and the specific content, parameter value and corresponding electronic device of each constraint condition are recorded in detail, so as to provide a comprehensive constraint basis for subsequent cable routing path planning.

[0148] Preferably, the cable routing path between the devices is planned based on the circuit performance, electromagnetic compatibility and spatial layout constraints between the corresponding electronic devices of the diode, the connector, the support and the threading hole, and a solar wing circuit device cable routing path is generated.

[0149] In the embodiment of the present application, the cable routing path is planned based on the circuit performance, electromagnetic compatibility and spatial layout constraints between the corresponding electronic devices of the diode, the connector, the support and the threading hole in the cable routing design module of the CAD software, and the path editing tool of the software is used to optimize each connection in the skeleton model. Taking the connection line from the P1 port of the diode D-01 to the P2 port of the connector CON-001 as an example, first, according to the circuit performance requirements, it is ensured that the specification of the cable can meet the current transmission demand, and a cable with a suitable diameter is selected, then, considering the electromagnetic compatibility constraints, the cable path is adjusted to be away from the devices sensitive to electromagnetic interference, and shielding measures are added, in terms of spatial layout, it is checked whether the cable path interferes with other devices according to the minimum distance requirement, if there is interference, adjustment is made by increasing the corner angle, changing the path direction and the like, in the planning process, the analysis function of the software is used in real time to check the electrical performance, electromagnetic compatibility and spatial layout of the cable path, for example, the electromagnetic radiation of the cable under different paths is simulated using the electromagnetic simulation module of the software to ensure that the electromagnetic compatibility constraints are met, after repeated adjustment and optimization, the cable routing path between all electronic devices is planned, and a solar wing circuit device cable routing path is generated, which records the starting point, end point, path shape, cable specification and satisfied constraint conditions and other information of each cable in detail, providing a precise and reliable cable routing scheme for the actual three-dimensional laying of the solar wing circuit.

[0150] Further, step S4 includes the following steps:

[0151] Step S41: The electrical logic connection analysis is performed according to the installation coordinates and wiring ports of the corresponding electronic devices of the diode, the connector, the support and the threading hole, to generate the corresponding device electrical wiring connection relationship between the electronic devices.

[0152] In the embodiment of the present application, by using the Python programming language combined with the pandas library, the electrical logic connection analysis is carried out according to the function and design requirements of the electronic device, and taking the diode numbered D-01 and the connector CON-001 as an example, it is clear from the relevant design documents that there is a series connection relationship between the two in the circuit, and the P1 port of the diode and the P2 port of the connector need to be electrically connected, and by writing a program to traverse all electronic devices, the connection relationship between the devices is judged according to the wiring port information and design logic, and for the devices with a connection relationship, the start and end port information of the connection is recorded, for example, if it is found that the resistance numbered R-01 and the diode D-01 have a parallel relationship, and the A port of the resistance and the P2 port of the diode are connected, then this connection relationship is recorded, and finally a dictionary containing the electrical connection relationship between all electronic devices is generated, such as {"D-01_P1":"CON-001_P2", "R-01_A":"D-01_P2",...}, and the dictionary is converted into a table form, which records in detail the corresponding device electrical wiring connection relationship between each electronic device, providing accurate electrical connection basis for subsequent operation.

[0153] Step S42: generating a corresponding electronic device device wiring node table based on the corresponding device electrical wiring connection relationship between each electronic device and combining the installation coordinates and wiring port connection of the corresponding electronic devices of the diode, the connector, the bracket and the threading hole;

[0154] In the embodiment of the present application, by continuing to use the pandas library in the Python environment, the electrical connection relationship between the electronic devices is integrated with the installation coordinates and wiring port information of the devices, and taking the connection relationship "D-01_P1":"CON-001_P2" as an example, the installation coordinates (300, 400) of the diode D-01 and the installation coordinates (500, 600) of the connector CON-001 are obtained from the installation coordinate table, and the detailed size and shape information of the diode P1 port and the connector P2 port are obtained from the wiring port table, these information is summarized to generate a new table record, which contains the connection starting device name (diode D-01), starting port (P1), starting port coordinates (300, 400), ending device name (connector CON-001), ending port (P2), ending port coordinates (500, 600) and other information, and the same method is used to process all electrical connection relationships, and finally a complete electronic device device wiring node table is generated, which comprehensively and detailedly records the connection information, installation position and port characteristics between electronic devices, providing key data support for the wiring modeling of the solar wing circuit.

[0155] Step S43: generate the corresponding solar wing circuit three-dimensional optimization entity model based on the electronic device wiring node table and combined with the solar wing circuit device cable routing path modeling;

[0156] In the embodiment of the present application, by opening the "solar wing circuit three-dimensional optimization entity model.Product" file in the CAD software, using the software's engineering drawing module, selecting the appropriate view direction (such as front view, side view, top view), the three-dimensional model is projected and converted to generate the corresponding solar wing circuit wiring laying two-dimensional drawing, in the process of generating two-dimensional drawing, set the appropriate scale (such as 1:10), mark clear size, tolerance and technical requirements. At the same time, using the software's attribute extraction function, export the solar wing circuit cable entity information from the three-dimensional model, for each cable, extract its belonging to the patch model (such as horizontal regional optimization patch model), type (such as RVV-2×1.5), starting and ending connection port (such as "D-01_P1":"CON-001_P2"), cable length (obtained by software measurement function, assuming 200mm) and cable quality information (according to the cable type and length, through the material density calculation, assuming 0.5kg), the cable entity information is arranged in table form, with the two-dimensional drawing of the solar wing circuit wiring laying, forming a complete set of solar wing circuit wiring laying design output, including the corresponding solar wing circuit wiring laying two-dimensional drawing and the corresponding solar wing circuit cable entity information.

[0157] Step S44: generate the corresponding solar wing circuit wiring laying two-dimensional drawing by the solar wing circuit three-dimensional optimization entity model wiring design output, and export the corresponding solar wing circuit cable entity information, including the corresponding belonging to the patch model, type, starting and ending connection port, cable length and cable quality information.

[0158] In the embodiment of the present application, by opening the "solar wing circuit three-dimensional optimization entity model.Product" file in the CAD software, using the software's engineering drawing module, selecting the appropriate view direction (such as front view, side view, top view), the three-dimensional model is projected and converted to generate the corresponding solar wing circuit wiring laying two-dimensional drawing, in the process of generating two-dimensional drawing, set the appropriate scale (such as 1:10), mark clear size, tolerance and technical requirements. At the same time, using the software's attribute extraction function, export the solar wing circuit cable entity information from the three-dimensional model, for each cable, extract its belonging to the patch model (such as horizontal regional optimization patch model), type (such as RVV-2×1.5), starting and ending connection port (such as "D-01_P1":"CON-001_P2"), cable length (obtained by software measurement function, assuming 200mm) and cable quality information (according to the cable type and length, through the material density calculation, assuming 0.5kg), the cable entity information is arranged in table form, with the two-dimensional drawing of the solar wing circuit wiring laying, forming a complete set of solar wing circuit wiring laying design output, including the corresponding solar wing circuit wiring laying two-dimensional drawing and the corresponding solar wing circuit cable entity information.Figure 1 The "solar wing circuit wiring layout drawing and cable information.dwg" file (two-dimensional drawing) and the "solar wing circuit cable entity information table.xlsx" file are saved, which provide detailed technical data and data support for the production, installation, debugging and maintenance of the solar wing circuit.

[0159] Further, the application also provides a solar wing circuit three-dimensional layout optimization system for executing the solar wing circuit three-dimensional layout optimization method as described above, which comprises:

[0160] A solar wing substrate modeling module is configured to acquire a solar wing substrate and construct ten sets of solar wing substrate layout models according to the solar wing substrate;

[0161] A substrate layout filtering module is configured to acquire the geometric shape parameters of the solar wing substrate, the circuit element parameters and the layout constraint conditions, and perform layout position deduction on the corresponding solar wing substrate layout model based on the geometric shape parameters of the solar wing substrate, the circuit element parameters and the layout constraint conditions to generate a corresponding set of solar wing layout position coordinates; and perform layout sorting filtering on the corresponding solar wing substrate layout model based on the set of solar wing layout position coordinates to generate an optimal solar wing layout model.

[0162] A circuit device path planning module is configured to acquire the installation coordinates and wiring ports of the corresponding electronic devices of the diodes, connectors, supports and threading holes, and perform cable wiring path planning on the installation coordinates and wiring ports of the corresponding electronic devices of the diodes, connectors, supports and threading holes in combination with the layout scheme of the optimal solar wing layout model to generate a solar wing circuit device cable routing path.

[0163] A three-dimensional entity wiring output module is configured to acquire a corresponding electronic device wiring node table according to the installation coordinates and wiring ports of the corresponding electronic devices of the diodes, connectors, supports and threading holes, and generate a corresponding solar wing circuit three-dimensional optimization entity model based on the electronic device wiring node table in combination with the solar wing circuit device cable routing path modeling; output a solar wing circuit wiring layout two-dimensional drawing from the solar wing circuit three-dimensional optimization entity model wiring design, and export corresponding solar wing circuit cable entity information.

[0164] Therefore, from any point of view, the embodiments should be regarded as exemplary and non-limiting, the scope of the application being defined by the appended claims rather than the above description, and it is intended to encompass all variations falling within the meaning and scope of the equivalent elements of the application file.

[0165] The foregoing is considered as illustrative only of the principles of the application. Numerous modifications and changes will readily occur to those skilled in the art, and it is intended to embrace all such modifications and changes that fall within the scope of the application. Accordingly, the application is not to be restricted in scope to the specific embodiments disclosed herein but is to be accorded the full scope that the principles and novel features request appropriately granted.

Claims

1. A method for three-dimensional routing optimization of solar wing circuits, characterized in that, The method comprises the following steps: Step S1: Obtain a solar wing substrate model sub-block, and construct ten sets of solar wing substrate patch models according to the solar wing substrate model sub-block; wherein, step S1 comprises the following steps: Step S11: Obtain a solar wing substrate model sub-block; Step S12: Arrange each solar wing substrate model sub-block along the substrate transverse direction, first fill the entire string of circuit elements in the center, and then determine whether the remaining area can be S-symmetrically patched according to the area, wherein the patching direction of the remaining area is from the center edge to both sides, to generate a transverse center priority symmetric patch model corresponding to the solar wing substrate; similarly, fill the entire string of circuit elements from both sides to the center along the substrate transverse direction, and determine whether the remaining area in the center can be S-symmetrically patched according to the area, wherein the patching direction of the remaining area is from both sides to the center, to generate a transverse two-side-to-center patch model corresponding to the solar wing substrate; similarly, fill the entire string of circuit elements from the center axis to both sides along the substrate transverse direction, and determine whether the remaining area on both sides can be S-symmetrically patched according to the area, wherein the patching direction of the remaining area is from the center to both sides, to generate a transverse center-axis-to-both-sides patch model corresponding to the solar wing substrate; Step S13: Transpose the patch model corresponding to step S12 along the substrate transverse direction to the longitudinal direction to generate three sets of longitudinal transposed patch models corresponding to the solar wing substrate; Step S14: Arrange each solar wing substrate model sub-block along the substrate transverse direction, cut the substrate into a middle row area, two side row areas, and a forbidden row area at a preset compression point, and fill the entire string of circuit elements in the middle row area and the two side row areas from the left side, supplement the flying patch in the forbidden row area, and determine whether the remaining area on the right side can be S-patched according to the area, to generate a transverse regional patch model corresponding to the solar wing substrate; transpose the transverse regional patch model along the substrate transverse direction to the longitudinal direction to generate a longitudinal transposed regional patch model corresponding to the solar wing substrate; Step S15: Use the transverse regional patch model as a blueprint to optimize the middle row area to preferentially fill the entire string of circuit elements in one direction, and use the maximum patch as the highest priority, to generate a transverse regional optimized patch model corresponding to the solar wing substrate; transpose the transverse regional optimized patch model along the substrate transverse direction to the longitudinal direction to generate a longitudinal transposed optimized patch model corresponding to the solar wing substrate; Step S2: Obtain solar wing substrate geometric shape parameters, circuit element parameters, and patch constraint conditions, and perform patch position deduction on the corresponding solar wing substrate patch model based on the solar wing substrate geometric shape parameters, circuit element parameters, and patch constraint conditions, to generate a corresponding solar wing patch position coordinate set; perform patch laying sorting and screening on the corresponding solar wing substrate patch model based on the solar wing patch position coordinate set, to generate an optimal solar wing patch laying model; wherein, step S2 comprises the following steps: Step S21: Obtain solar wing substrate geometric shape parameters, including the length, width, and thickness of the solar wing substrate; Step S22: Obtain circuit element parameters, including the size, shape, and number of circuit elements; Step S23: Obtain the cloth constraint conditions corresponding to the solar wing substrate, including the above ten sets of cloth model corresponding forbidden cloth area constraints and whether to meet the S-shaped cloth constraint; Step S24: Based on the solar wing substrate geometric shape parameters, circuit element parameters and cloth constraint conditions, the corresponding solar wing substrate cloth model is deduced to generate the corresponding solar wing cloth position coordinate set; Step S25: Based on the solar wing cloth position coordinate set, the corresponding solar wing substrate cloth model is laid out and sorted to generate the solar wing optimal laid cloth model; Step S3: Obtain the installation coordinates and wiring ports of the corresponding electronic devices of diodes, connectors, supports and threading holes, and combine the cloth scheme corresponding to the solar wing optimal laid cloth model to plan the cable wiring path of the corresponding electronic devices of diodes, connectors, supports and threading holes, to generate the solar wing circuit device cable wiring path; Step S4: Obtain the corresponding electronic device wiring node table according to the installation coordinates and wiring ports of the corresponding electronic devices of diodes, connectors, supports and threading holes, and generate the corresponding solar wing circuit three-dimensional optimization entity model based on the electronic device wiring node table and the solar wing circuit device cable wiring path modeling; output the corresponding solar wing circuit wiring laying two-dimensional graph by the solar wing circuit three-dimensional optimization entity model wiring design, and export the corresponding solar wing circuit cable entity information.

2. The solar wing circuit three-dimensional layup optimization method of claim 1, wherein, Step S24 includes the following steps: Step S241: Based on the cloth constraint conditions, the cloth space limitation analysis is performed on the corresponding solar wing substrate cloth model to obtain the corresponding solar wing substrate forbidden cloth area space limitation relationship; Step S242: Based on the solar wing substrate geometric shape parameters and circuit element parameters, and combining the corresponding solar wing substrate forbidden cloth area space limitation relationship, the available geometry planning is performed to adjust the cloth arrangement position between the available area of the substrate and the corresponding size and quantity of the matched circuit element by using the heuristic search method, to generate the corresponding solar wing substrate available cloth position layout graph; Step S243: Based on the S-shaped cloth constraint in the cloth constraint condition, the cloth position local optimization is performed on the corresponding solar wing substrate available cloth position layout graph to adjust the local position of the cloth based on the S-shaped cloth constraint and the minimum rotation angle, to generate the corresponding solar wing substrate cloth optimization layout graph; Step S244: Based on the solar wing substrate cloth optimization layout graph, the cloth position deduction is performed on the corresponding solar wing substrate cloth model to generate the corresponding solar wing cloth position coordinate set.

3. The solar wing circuit 3D layup optimization method of claim 2, wherein, Step S244 includes the following steps: The corresponding solar wing substrate layout coordinate system is established through the solar wing substrate cloth optimization layout graph; Based on the solar wing substrate layout coordinate system, the geometric transformation deduction calculation is performed on each cloth in the solar wing substrate cloth optimization layout graph to calculate the center coordinates, angles and relative position points of each cloth in the solar wing substrate graph; The position of each panel in the solar wing substrate is deduced based on the center coordinates, angles and relative position points of each panel in each solar wing substrate map, to generate a corresponding set of solar wing panel position coordinates.

4. The solar wing circuit 3-D routing optimization method of claim 1, wherein, Step S25 includes the following steps: Step S251: Calculate the effective area of each solar wing panel according to the set of solar wing panel position coordinates; Step S252: Obtain the total area of the solar wing substrate, and calculate the panel rate corresponding to each solar wing panel model based on the ratio between the effective area of the solar wing panel and the total area of the solar wing substrate; Step S253: Sort and screen the corresponding solar wing substrate panel model based on the panel rate corresponding to each solar wing panel model, in descending order, and select the solar wing panel model with the largest panel rate as the optimal model to generate the optimal solar wing panel layout model.

5. The solar wing circuit three-dimensional routing optimization method of claim 1, wherein, Step S3 includes the following steps: Step S31: Obtain the installation coordinates of the diode, connector, support and threading hole corresponding electronic devices; Step S32: Obtain the wiring port of the diode, connector, support and threading hole corresponding electronic devices; Step S33: Create a three-dimensional model of the device according to the installation coordinates and wiring port of the diode, connector, support and threading hole corresponding electronic devices, to generate a solar wing circuit device three-dimensional model; Step S34: Plan the cable routing path of the solar wing circuit device by combining the solar wing circuit device three-dimensional model with the solar wing optimal panel layout model corresponding to the panel scheme, to generate the solar wing circuit device cable routing path.

6. The solar wing circuit three-dimensional routing optimization method of claim 5, wherein, Step S34 includes the following steps: Process the panel port wiring between each electronic device in the solar wing circuit device three-dimensional model by combining the solar wing optimal panel layout model corresponding to the panel scheme, to obtain a panel port wiring skeleton model between the solar wing circuit devices; Obtain the circuit performance, electromagnetic compatibility and spatial layout constraints between the diode, connector, support and threading hole corresponding electronic devices; Plan the cable routing path between the devices based on the circuit performance, electromagnetic compatibility and spatial layout constraints between the diode, connector, support and threading hole corresponding electronic devices, to generate the solar wing circuit device cable routing path.

7. The solar wing circuit 3-D routing optimization method of claim 1, wherein, Step S4 includes the following steps: Step S41: Perform electrical logic connection analysis according to the installation coordinates and wiring port of the diode, connector, support and threading hole corresponding electronic devices, to generate the corresponding device electrical wiring connection relationship between each electronic device; Step S42: Generate a corresponding electronic device wiring node table based on the device electrical wiring connection relationship between each electronic device and combining the installation coordinates and wiring port of the diode, connector, support and threading hole corresponding electronic devices; Step S43: Generate a corresponding solar wing circuit three-dimensional optimization entity model based on the electronic device wiring node table and combining the solar wing circuit device cable routing path modeling. Step S44: output the corresponding solar wing circuit wiring laying two-dimensional diagram by the solar wing circuit three-dimensional optimization entity model wiring design, and export the corresponding solar wing circuit cable entity information, including the corresponding belonging to the cloth model, model, starting and ending connection port, cable length and cable quality information.

8. A solar wing circuit three-dimensional layup optimization system, characterized by, The solar wing circuit three-dimensional laying optimization system is used for executing the solar wing circuit three-dimensional laying optimization method as claimed in claim 1, and comprises: A solar wing cloth modeling module is used for acquiring a solar wing substrate and constructing ten sets of solar wing substrate cloth models according to the solar wing substrate. A substrate laying cloth screening module is used for acquiring the solar wing substrate geometric shape parameters, circuit element parameters and cloth constraint conditions, and performing cloth position deduction on the corresponding solar wing substrate cloth models based on the solar wing substrate geometric shape parameters, circuit element parameters and cloth constraint conditions to generate a corresponding solar wing cloth position coordinate set; and performing laying cloth sorting screening on the corresponding solar wing substrate cloth models based on the solar wing cloth position coordinate set to generate a solar wing optimal laying cloth model. A circuit device path planning module is used for acquiring the installation coordinates and connection ports of the diodes, connectors, supports and threading holes corresponding to the electronic devices, and performing cable wiring path planning on the installation coordinates and connection ports of the diodes, connectors, supports and threading holes corresponding to the electronic devices in combination with the cloth scheme of the solar wing optimal laying cloth model to generate a solar wing circuit device cable wiring path. A three-dimensional entity wiring output module is used for acquiring the corresponding electronic device device connection node table according to the installation coordinates and connection ports of the diodes, connectors, supports and threading holes corresponding to the electronic devices, and generating a corresponding solar wing circuit three-dimensional optimization entity model based on the electronic device device connection node table in combination with the solar wing circuit device cable wiring path modeling; outputting the corresponding solar wing circuit wiring laying two-dimensional diagram by the solar wing circuit three-dimensional optimization entity model wiring design, and exporting the corresponding solar wing circuit cable entity information.

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