Statically indeterminate structure multi-intersection load analysis method

Abstract

The invention belongs to the field of airplane structure load analysis, and particularly relates to a statically indeterminate structure multi-intersection-point load analysis method. The statically indeterminate structure multi-intersection-point load analysis method based on the finite element is provided for the common multi-intersection-point component butt joint problem in an aircraft structure in combination with the structural design scheme design, preliminary design, detailed design and design improvement stages, and accurate loads can be rapidly obtained to be used for structural design in different stages.

Description

Technical Field

[0001] This application belongs to the field of aircraft structural load analysis, and specifically relates to a multi-intersection load analysis method for statically indeterminate structures. Background Technology

[0002] In existing aircraft structural design, the concentrated intersection docking method is widely used in the assembly design of large components, especially wing-body docking structures, due to its advantages of light weight and clear force transmission path. For concentrated intersection docking, the most crucial aspect is the accurate load at the intersection points. The docking of large components typically employs multiple sets of intersection points, forming a statically indeterminate docking structure. The loads distributed across each set of intersection points cannot be obtained through simple engineering estimation and often require the use of finite element analysis.

[0003] Traditional methods for obtaining intersection loads involve calculating them using a simplified plate-and-bar natural mesh finite element model. The joints at concentrated intersections are represented by a limited number of plate-and-bar elements, and the mesh near the intersections is also a natural mesh. This model cannot accurately simulate the stiffness of the intersections, nor can it accurately reflect the structural stiffness near the intersections, while the loads at the intersections are closely related to the stiffness of the concentrated intersection joints and the surrounding structure. This leads to significant uncertainties in the intersection loads calculated using the plate-and-bar model, easily causing inaccurate calculations. Furthermore, it results in repeated and uncontrollable variations in the intersection loads. Structures designed using inaccurate loads may not only carry certain risks, but the repeated load variations also reduce structural design efficiency and lengthen the design cycle, which contradicts current requirements for short-cycle design.

[0004] Therefore, there is an urgent need for a technical solution to overcome or mitigate at least one of the aforementioned defects in the existing technology. Summary of the Invention

[0005] The purpose of this application is to provide a method for analyzing multi-intersection loads of statically indeterminate structures to solve at least one problem existing in the prior art.

[0006] The technical solution of this application is:

[0007] The first aspect of this application provides a method for multi-intersection load analysis of statically indeterminate structures, including:

[0008] Step 1: Obtain the structural layout skeleton model and load data;

[0009] Step 2: Construct a full-machine natural mesh finite element model based on the structural layout skeleton model;

[0010] Step 3: Map the load data onto the full-machine natural mesh finite element model, perform the first round of parameter optimization, and obtain the first round of intersection load and the first round of parameter optimization results;

[0011] Step 4: Select the intersection structure scheme based on the intersection load of the first round and the parameter optimization results of the first round, and determine the intersection structure design scheme;

[0012] Step 5: Construct a detailed simulation model of the intersection point according to the intersection point structure design scheme, and embed the detailed simulation model of the intersection point into the whole machine natural mesh finite element model to obtain a preliminary nested model. Perform the second round of parameter optimization to obtain the second round of intersection point load and the second round of parameter optimization results.

[0013] Step 6: Based on the intersection load of the second round and the parameter optimization results of the second round, perform detailed design of the intersection structure and obtain the detailed design results of the intersection structure;

[0014] Step 7: Based on the detailed design results of the intersection structure, construct detailed models of the intersection structure and surrounding structure box segments, and embed the detailed models of the intersection structure and surrounding structure box segments into the full-machine natural mesh finite element model to obtain a detailed nested model. Perform the third round of parameter optimization to obtain the third round of intersection load and the third round of parameter optimization results.

[0015] Step 8: Design and issue drawings for the intersection structure and surrounding structure based on the third round of intersection loads;

[0016] Step 9: Based on the structural model of the intersection structure and surrounding structure after the design drawings are issued, construct a refined finite element model of the whole machine, perform the fourth round of parameter optimization, and obtain the fourth round of intersection loads;

[0017] Step 10: Compare the intersection load of the third round with the intersection load of the fourth round to determine whether the intersection structure and the surrounding structure after the design drawings are issued meet the design requirements.

[0018] In at least one embodiment of this application, in step one, the structural layout skeleton model includes load-bearing component information, structural separation surface division information, preliminary determination information of intersection connection positions, component position information, and component type information.

[0019] In at least one embodiment of this application, in step one, the load data includes the load size, load application point / distribution location, and load usage conditions corresponding to each load type under different load conditions.

[0020] In at least one embodiment of this application, the load type includes aerodynamic load, fuel load, inertial load, and engine load.

[0021] In at least one embodiment of this application, in step two, in the whole machine natural mesh finite element model, each component position is used as a division, the area enclosed by the intersection between components is a plate element, the boundary between components is simulated by rod elements, components are connected by common nodes, and all nodes are naturally generated by the intersection of component planes.

[0022] In at least one embodiment of this application, in step three, the load data is mapped and loaded onto the nodes of the full-machine natural mesh finite element model using the Lagrange multiplier method or the aerodynamic equivalent method.

[0023] In at least one embodiment of this application, step three, the first round of parameter optimization includes skin thickness optimization and beam / frame area optimization.

[0024] In at least one embodiment of this application, in step five, a three-dimensional solid element is used to simulate the intersection structure in the intersection detail simulation model, and the intersection structure is provided with nail holes.

[0025] In at least one embodiment of this application, in step seven, the detailed model of the intersection structure and the surrounding structure box segment includes the surrounding structure within a preset range of the intersection structure, three-dimensional solid elements are used to simulate the intersection structure and the force transmission structure, and plate and shell elements are used to simulate the structure other than the intersection structure and the force transmission structure.

[0026] In at least one embodiment of this application, in step seven, when embedding the detailed model of the intersection structure and the surrounding structure box segment into the full-machine natural mesh finite element model, the natural mesh cells corresponding to the detailed model of the intersection structure and the surrounding structure box segment are deleted.

[0027] In at least one embodiment of this application, in step nine, in the refined finite element model of the whole machine, three-dimensional solid elements are used to simulate the intersection structure, key connection joints and complex stress structure, plate and shell elements are used to simulate the structure other than the intersection structure, key connection joints and complex stress structure, and beam elements are used to simulate fasteners.

[0028] In at least one embodiment of this application, the three-dimensional solid unit is a hexahedral unit or a tetrahedral unit.

[0029] A second aspect of this application provides an electronic device including a memory, a processor, and a computer program stored in the memory and capable of running on the processor, wherein the processor executes the computer program to implement the method for analyzing multi-intersection loads of statically indeterminate structures as described above.

[0030] A third aspect of this application provides a computer-readable storage medium storing a computer program that, when executed by a processor, enables the implementation of the multi-intersection load analysis method for statically indeterminate structures as described above.

[0031] The invention has at least the following beneficial technical effects:

[0032] The multi-intersection load analysis method for statically indeterminate structures proposed in this application can accurately and quickly analyze the intersection loads of statically indeterminate structures with multiple intersection points. Attached Figure Description

[0033] Figure 1 This is a flowchart of a method for analyzing multi-intersection loads of statically indeterminate structures according to one embodiment of this application;

[0034] Figure 2 This is a schematic diagram of a full-machine natural mesh finite element model according to one embodiment of this application;

[0035] Figure 3 This is a schematic diagram of the rbe3 connection, which is a simulation model of the intersection details including fastener holes, according to one embodiment of this application.

[0036] Figure 4 This is a schematic diagram of the connection of the rbe3, a simulation model of the intersection details without fastener holes, according to one embodiment of this application. Detailed Implementation

[0037] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0038] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of this application.

[0039] The following is in conjunction with the appendix Figures 1 to 4 This application will be described in further detail.

[0040] This application provides a method for multi-intersection load analysis of statically indeterminate structures, including the following steps:

[0041] Step 1: Obtain the structural layout skeleton model and load data.

[0042] Acquire load data, including aerodynamic loads, fuel loads, inertial loads, and engine loads, under various loading conditions from the structural layout skeleton model and the overall professional specifications. The structural layout skeleton model includes information on load-bearing components, structural separation surface divisions, preliminary determination of intersection connection locations, component positioning information, and component type information. The load data includes the load magnitude, load application point / distribution location, and load usage conditions for each load type under different loading conditions.

[0043] Step 2: Construct a full-machine natural mesh finite element model based on the structural layout skeleton model.

[0044] In the full-machine natural mesh finite element model, each component station is used as a division. The area enclosed by the intersection between components is a CQUAD4 or CTRIA3 plate element. The boundary between components is simulated using CROD or CBAR rod elements. Components are connected by common nodes. All nodes are naturally generated by the intersection of the component planes.

[0045] Regions with similar length and width that must be considered for shear effects are simulated using plate elements. Components that primarily transmit axial loads and do not consider out-of-plane effects or shear effects are simplified to CBAR rod element simulations. The connection between the intersection structure and components is achieved by using both plate and rod elements, connecting to at least three nearby non-collinear nodes, ensuring that the intersection does not have a situation where out-of-plane degrees of freedom are completely released.

[0046] Step 3: Map the load data onto the full-machine natural mesh finite element model, perform the first round of parameter optimization, and obtain the first round of intersection loads and the first round of parameter optimization results.

[0047] Using the Lagrange multiplier method or aerodynamic equivalent method, the aerodynamic loads, inertial loads, and other load data published by the overall discipline are mapped onto the nodes of the full-aircraft natural mesh finite element model, and then parameter optimization analysis is carried out. Under the constraints of the design conditions, the full-aircraft / segment optimization analysis based on the natural mesh model is completed. The optimization analysis includes skin thickness optimization analysis and beam / frame area optimization analysis, and the first round of intersection loads at each concentrated intersection point are obtained.

[0048] Step 4: Select the intersection structure scheme based on the intersection load of the first round and the parameter optimization results of the first round, and determine the intersection structure design scheme.

[0049] Based on the load of the first round of intersection and the results of the first round of parameter optimization, the structural scheme selection and design work of each intersection and the sample design work of the surrounding structure of the intersection are completed, and the structural design scheme of the intersection is determined.

[0050] Step 5: Construct a detailed simulation model of the intersection point based on the intersection point structure design scheme, and embed the detailed simulation model of the intersection point into the full-machine natural mesh finite element model to obtain a preliminary nested model. Perform the second round of parameter optimization to obtain the second round of intersection point load and the second round of parameter optimization results.

[0051] The detailed simulation model of the intersection point is built using 3D solid elements, with CHEXA hexahedral elements being the preferred choice and second-order CTETRA tetrahedral elements as a secondary option. The intersection structure needs to include nail holes, which are connected to the natural mesh model via RBE3+cbar+RBE3 elements to simulate fastener connections. If the natural mesh at the nail point location lacks corresponding nodes, the natural mesh should be locally refined using the nodes corresponding to the nail point. At least three nearest non-collinear nodes in the detailed intersection structure model should be bound to the nail point via RBE3 elements. The thickness parameters of the surrounding structure are then updated, and a second round of simulation optimization is conducted.

[0052] Step 6: Based on the second round of intersection load and the second round of parameter optimization results, perform detailed design of the intersection structure and obtain the detailed design results of the intersection structure.

[0053] Conduct detailed design work on the intersection structure and its surrounding related structures, design reasonable load transfer paths, and optimize the structure itself.

[0054] Step 7: Based on the detailed design results of the intersection structure, construct detailed models of the intersection structure and surrounding structure box segments, and embed the detailed models of the intersection structure and surrounding structure box segments into the full-machine natural mesh finite element model to obtain a detailed nested model. Perform the third round of parameter optimization to obtain the third round of intersection load and the third round of parameter optimization results.

[0055] The detailed model of the intersection structure and surrounding structure box segments includes the surrounding structures within the preset range of the intersection structure. Three-dimensional solid elements are used to simulate the intersection structure and the force transmission structure, while plate and shell elements are used to simulate structures other than the intersection structure and the force transmission structure. The detailed finite element model range includes related structures at least three times the maximum contour distance from the intersection point. Except for the intersection structure and complex force transmission structures, which should be simulated using three-dimensional solid elements, all other structures are simulated using plate and shell elements. The preferred solid element is the CHEXA hexahedral element, and the secondary is the second-order CTETRA tetrahedral element; the preferred plate and shell element is CQUAD4, and the secondary is CTRIA3.

[0056] Fastener holes should be made for intersection structures, critical connection joints, and their directly connected structures. In the box segment detail model, all components are connected using RBE3+cbar+RBE3 to simulate fastener connections. In areas with fastener holes, cbar elements should be bound to the nodes around the fastener hole using rbe3 elements; in areas without fastener holes, cbar element nodes should be bound to at least three nearest non-collinear nodes of the detail model using rbe3 elements. When embedding the intersection structure and surrounding structure box segment detail models into the full-machine natural mesh finite element model, the natural mesh elements corresponding to the intersection structure and surrounding structure box segment detail models are deleted. The connection between the detail model and the natural mesh model is made using GMBNDC+CINTC elements.

[0057] Step 8: Design and issue drawings for the intersection structure and surrounding structure based on the intersection load of the third round.

[0058] Based on the intersection load calculated in step seven, the design load for drawing is used to complete the digital model design and release of the intersection structure and its associated surrounding structures.

[0059] Step 9: Based on the structural model of the intersection structure and surrounding structure after the design drawings are issued, construct a refined finite element model of the whole machine, perform the fourth round of parameter optimization, and obtain the fourth round of intersection load.

[0060] In the refined finite element model of the entire machine, three-dimensional solid elements are used to simulate intersection structures, key connection joints, and complex stress structures. Shell elements are used to simulate structures other than intersection structures, key connection joints, and complex stress structures. Beam elements are used to simulate fasteners. Except for intersection structures, key connection joints, and areas with complex stresses, which are discretized into three-dimensional solid elements, all other parts are discretized into shell elements. Except for fasteners, which are simulated using Cbar beam elements, other components are not allowed to be simplified to rod elements. Fastener holes should be made in intersection structures, key connection joints, and their directly connected structures. The preferred solid element is the CHEXA hexahedral element, and the secondary option is the second-order CTETRA tetrahedral element; the preferred shell element is CQUAD4, and the secondary option is CTRIA3. In the full-scale refined finite element model, all components are connected using RBE3+cbar+RBE3 to simulate fastener connections. In areas with fastener holes, cbar elements should be bound to nodes around the fastener holes via rbe3 elements. In areas without fastener holes, cbar element nodes should be bound to at least three nearest non-collinear nodes of the detail model via rbe3 elements.

[0061] Step 10: Compare the intersection loads of the third and fourth rounds to determine whether the intersection structure and surrounding structure after the design drawings are issued meet the design requirements.

[0062] By comparing the intersection loads of the third and fourth rounds, and reviewing whether the intersection structure and surrounding structures after the design were issued meet the design requirements, the intersection load analysis work is now complete.

[0063] The following section uses the multi-intersection load analysis of an airfoil structure as an example to illustrate the process of this application:

[0064] Step 1: Obtain the wing structural layout skeleton model and the load data (aerodynamic load, fuel load, inertial load, engine load, etc.) under various load conditions released by the overall professional team. The wing structural layout skeleton model includes the wing-body docking point location information.

[0065] Step 2: Based on the wing structure layout skeleton model, and using beams, wing ribs, and stringers as the skeleton separation surfaces, establish a full-aircraft natural mesh finite element model. The wing-body docking intersection uses a plate-rod model, and the plate-rod elements are connected through four non-coplanar intersection points.

[0066] In this design, beams and girder are used as longitudinal segments, and ribs are used as transverse segments. The naturally segmented and discrete areas of the skin are defined as a plate element. The intersections of beams, girder, skin, and ribs are used to establish crod elements. The girder is simplified to a crod rod element, and the skin is a CQUAD4 or CTRIA3 plate and shell element.

[0067] Step 3: Map the aerodynamic loads published by the overall discipline onto the full-aircraft natural mesh finite element model, complete the first round of preliminary optimization analysis of the skin, wing ribs and beam web thickness and stringer and strut area parameters, and obtain the loads at each wing-body docking point in the first round.

[0068] Step 4: Based on the results of the first round of intersection load and parameter optimization, complete the structural scheme selection and design work for the wing-body docking intersection and the prototype design work for the connected panel and wing rib structures.

[0069] Step 5: Based on the wing-body docking intersection structure design scheme in Step 4, establish a detailed simulation model of the wing-body docking structure and embed it into the full-aircraft natural mesh finite element model established in Step 2. The wing-body docking structure is simulated using second-order CTETRA tetrahedral elements, and fastener holes are made on the joint. It is connected to the natural mesh model via RBE3+cbar+RBE3 to simulate fastener connections. If the natural mesh at the corresponding position of the nail point does not have a corresponding node, the natural mesh is locally refined, and the four nearest non-collinear nodes of the natural mesh model are bound to the nail point via RBE3 elements. Update the thickness parameters of the surrounding structure and obtain the second round of load and parameter optimization results for each intersection point.

[0070] Step Six: Based on the intersection load and parameter optimization results from Step Five, conduct detailed design work on the wing-body docking intersection structure and the surrounding associated skin, ribs, and spars, and design a reasonable load transfer path.

[0071] Step 7: Based on the detailed digital model of the wing-body docking joint and surrounding structure obtained in Step 6, select the relevant structures with the largest profiles three rib distances from the intersection point and establish a detailed finite element model of the box segment. Fastener holes are retained for all components connected to the wing-body docking structure. Connections between any two components, such as beams, wing ribs, panels, and joints, are simulated using the RBE3+cBar+RBE3 method. In areas with fastener holes, cbar elements should be bound to nodes around the fastener holes using rbe3 elements; in areas without fastener holes, cbar element nodes should be bound to at least three nearest non-collinear nodes of the detailed model using rbe3 elements.

[0072] The natural mesh elements corresponding to the box segment detailed model should be deleted, and the connection between the box segment detailed model and the natural mesh model should be made using GMBNDC+CINTC elements. Then, optimization analysis is performed, and the optimization results of the third round of intersection loads and surrounding structural parameters are obtained.

[0073] Step 8: Using the intersection loads calculated from the local detail model obtained in Step 7 as the design loads for the drawings, complete the design and release of the digital model of the intersection structure and its associated wall panels, beams, and ribs.

[0074] Step Nine: Based on the structural digital model released after the design is completed, establish a refined finite element model of the entire aircraft. Except for the wing-fuselage docking joint, which is simulated using CHEXA hexahedral elements, the panels, beams, ribs, stringers, etc., are all discretized into shell element detail models. The connections between the parts are simulated using the RBE3+cBar+RBE3 method. In areas with fastener holes, cbar elements should be bound to the nodes around the fastener holes using rbe3 elements; in areas without fastener holes, cbar element nodes should be bound to at least three nearest non-collinear nodes of the detail model using rbe3 elements. Conduct optimization analysis and obtain the fourth round of intersection loads.

[0075] Step 10: Compare the intersection loads from the fourth round with those from the third round, and review whether the intersection structure and surrounding structures after the design release meet the design requirements. At this point, the intersection loads have been determined.

[0076] This application presents a rapid analysis method for multi-intersection loads on statically indeterminate structures. For multiple sets of concentrated intersection joints, it employs a multi-step, progressively refined research approach. Based on different structural design stages, it establishes matching finite element models to gradually obtain the most realistic possible intersection loads. The methods are as follows: **Scheme Design Stage:** A natural mesh model is established to obtain the first round of intersection loads, and scheme selection and parameter optimization are carried out. **Preliminary Design Stage:** The intersection joints are established as solid models, embedded in the natural mesh model, and the second round of intersection loads is obtained. Optimization design of the intersection structure and surrounding structures begins. **Detailed Design Stage:** Detailed models of the optimized intersection structure and surrounding structures at more distant locations are established, embedded in the natural mesh model, and the third round of intersection loads is obtained for optimization of the intersection structure and surrounding structures and for the release of digital models. **Review Stage:** A full-scale detailed finite element model is established. All structures are discretized into detailed models, and solid models of the intersections and necessary surrounding structures are established to accurately simulate their stiffness. A quality review is conducted after drawing release, and any unsatisfactory strength or stiffness requirements are promptly corrected.

[0077] This application addresses the common problem of multi-intersection component docking in aircraft structures. Combining structural design scheme design, preliminary design, detailed design, and design refinement stages, it proposes a finite element method for multi-intersection load analysis of statically indeterminate structures. This method can quickly obtain accurate loads for use in structural design at different stages. This application solves the following problems:

[0078] 1) Solve the problem that the load at the intersection of traditional plate and rod models has a large error compared with the actual load, making it difficult to obtain accurate loads for detailed structural design and thus preventing the model from being finalized;

[0079] 2) The modeling and analysis method of nesting detailed model and natural mesh model is used to solve the problem of slow iteration of multi-intersection load caused by slow iteration of finite element model, which leads to lag in structural design.

[0080] 3) Obtain accurate intersection loads at each stage to solve the problems of large differences between plate and rod models and detailed models, which lead to a large amount of repetitive work after the structural design is completed, and the lack of effective and accurate input of intersection loads, which leads to repeated iterations of structural design and a long structural design cycle.

[0081] This application presents a rapid analysis method for multi-intersection loads on statically indeterminate structures, applicable to the analysis and structural design of multi-intersection loads on all aircraft employing multiple sets of concentrated intersection point connections. Compared to existing technologies, this application effectively improves the accuracy of intersection loads. Each round of intersection loads is a usable effective load in the structural design phase, significantly reducing iterative structural design and improving design efficiency while effectively ensuring structural safety and minimizing structural weight. Furthermore, by using model embedding, it minimizes the workload caused by repeated changes in the finite element model resulting from iterative structural design.

[0082] A second aspect of this application provides an electronic device including a memory, a processor, and a computer program stored in the memory and capable of running on the processor, wherein the processor executes the computer program to implement the above-described method for analyzing multi-intersection loads of statically indeterminate structures.

[0083] A third aspect of this application provides a computer-readable storage medium storing a computer program that, when executed by a processor, enables the implementation of the above-described method for analyzing multi-intersection loads of statically indeterminate structures.

[0084] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A method for analyzing multi-intersection loads on statically indeterminate structures, characterized in that, include: Step 1: Obtain the structural layout skeleton model and load data; Step 2: Construct a full-machine natural mesh finite element model based on the structural layout skeleton model; Step 3: Map the load data onto the full-machine natural mesh finite element model, perform the first round of parameter optimization, and obtain the first round of intersection load and the first round of parameter optimization results; Step 4: Select the intersection structure scheme based on the intersection load of the first round and the parameter optimization results of the first round, and determine the intersection structure design scheme; Step 5: Construct a detailed simulation model of the intersection point according to the intersection point structure design scheme, and embed the detailed simulation model of the intersection point into the whole machine natural mesh finite element model to obtain a preliminary nested model. Perform the second round of parameter optimization to obtain the second round of intersection point load and the second round of parameter optimization results. Step 6: Based on the intersection load of the second round and the parameter optimization results of the second round, perform detailed design of the intersection structure and obtain the detailed design results of the intersection structure; Step 7: Based on the detailed design results of the intersection structure, construct detailed models of the intersection structure and surrounding structure box segments, and embed the detailed models of the intersection structure and surrounding structure box segments into the full-machine natural mesh finite element model to obtain a detailed nested model. Perform the third round of parameter optimization to obtain the third round of intersection load and the third round of parameter optimization results. Step 8: Design and issue drawings for the intersection structure and surrounding structure based on the third round of intersection loads; Step 9: Based on the structural model of the intersection structure and surrounding structure after the design drawings are issued, construct a refined finite element model of the whole machine, perform the fourth round of parameter optimization, and obtain the fourth round of intersection loads; Step 10: Compare the intersection load of the third round with the intersection load of the fourth round to determine whether the intersection structure and the surrounding structure after the design drawings are issued meet the design requirements.

2. The method for analyzing multi-intersection loads of statically indeterminate structures according to claim 1, characterized in that, In step one, the structural layout skeleton model includes information on load-bearing components, information on the division of structural separation surfaces, information on the preliminary determination of intersection connection positions, information on component positions, and information on component types.

3. The method for analyzing multi-intersection loads of statically indeterminate structures according to claim 2, characterized in that, In step one, the load data includes the load size, load application point / distribution location, and load usage conditions corresponding to each load type under different load conditions.

4. The method for analyzing multi-intersection loads of statically indeterminate structures according to claim 3, characterized in that, The load types include aerodynamic loads, fuel loads, inertial loads, and engine loads.

5. The method for analyzing multi-intersection loads of statically indeterminate structures according to claim 4, characterized in that, In step two, in the full-machine natural mesh finite element model, each component station is used as a division, the area enclosed by the intersection between components is a plate element, the boundary between components is simulated by rod elements, components are connected by common nodes, and all nodes are naturally generated by the intersection of component planes.

6. The method for multi-intersection load analysis of statically indeterminate structures according to claim 5, characterized in that, In step three, the load data is mapped and loaded onto the nodes of the full-machine natural mesh finite element model using the Lagrange multiplier method or the aerodynamic equivalent method.

7. The method for multi-intersection load analysis of statically indeterminate structures according to claim 6, characterized in that, In step three, the first round of parameter optimization includes skin thickness optimization and beam / frame area optimization.

8. The method for analyzing multi-intersection loads of statically indeterminate structures according to claim 7, characterized in that, In step five, the intersection structure is simulated using three-dimensional solid elements in the intersection detail simulation model, and the intersection structure is provided with nail holes.

9. The method for analyzing multi-intersection loads of statically indeterminate structures according to claim 8, characterized in that, In step seven, the detailed model of the intersection structure and the surrounding structure box segment includes the surrounding structure within the preset range of the intersection structure. Three-dimensional solid elements are used to simulate the intersection structure and the force transmission structure, and plate and shell elements are used to simulate the structure other than the intersection structure and the force transmission structure.

10. The method for multi-intersection load analysis of statically indeterminate structures according to claim 9, characterized in that, In step seven, when embedding the detailed model of the intersection structure and the surrounding structure box segment into the full-machine natural mesh finite element model, the natural mesh elements corresponding to the detailed model of the intersection structure and the surrounding structure box segment are deleted.

11. The method for multi-intersection load analysis of statically indeterminate structures according to claim 10, characterized in that, In step nine, in the refined finite element model of the whole machine, three-dimensional solid elements are used to simulate the intersection structure, key connection joints and complex stress structure, plate and shell elements are used to simulate the structure other than the intersection structure, key connection joints and complex stress structure, and beam elements are used to simulate fasteners.

12. The method for multi-intersection load analysis of statically indeterminate structures according to claim 11, characterized in that, The three-dimensional solid unit is a hexahedral unit or a tetrahedral unit.

13. An electronic device comprising a memory, a processor, and a computer program stored in the memory and capable of running on the processor, characterized in that, When the processor executes the computer program, it implements the method for analyzing multi-intersection loads of statically indeterminate structures as described in any one of claims 1 or 12.

14. A computer-readable storage medium storing a computer program, characterized in that, When the computer program is executed by the processor, it can implement the multi-intersection load analysis method for statically indeterminate structures as described in any one of claims 1 or 12.

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