Aircraft body structure fluid-thermal-solid coupling analysis method

Abstract

The invention belongs to the technical field of aviation aircraft body structure design, and particularly relates to an aviation aircraft body structure fluid-thermal-solid coupling analysis method which comprises the following steps: step 1, establishing a body structure geometric model; step 2, performing pneumatic grid division on the geometric model of the airframe structure, and synchronously completing structural grid division in the process of establishing an external heat flow field of the airframe structure; step 3, performing flow field analysis on the engine body structure, and completing external temperature field analysis and internal heat transfer analysis based on external heat flow field boundary conditions; step 4, carrying out individual structure grid division on the geometric model of the engine body structure, and mapping a flow field analysis thermal load to a structure grid; and 5, carrying out force field analysis on the body structure, wherein the force field analysis comprises static analysis, vibration characteristic analysis and modal analysis.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft body structure design, and specifically relates to a fluid-thermal-solid coupling analysis method for aircraft body structure. Background Art

[0002] The design of aircraft fuselage structure involves fluid-heat-solid analysis of the structure. Due to the large size of aircraft fuselage structure, such as the rear nozzle, wing, fuselage, etc., and the complex internal structure, the current fluid-heat-solid analysis of the fuselage structure usually firstly conducts external flow field analysis based on the structure shape and flight profile by aerodynamic professionals to obtain the adiabatic wall temperature and isothermal wall heat flux on the structure surface, and then the structural professionals conduct convective boundary conversion on the structure based on the upstream heat load, and complete transient thermal analysis. Finally, the transient thermal analysis results are used as boundary input to conduct force field analysis, including static analysis, vibration characteristics analysis, etc. This analysis method has the following defects:

[0003] 1) The calculation of thermal load by aerodynamic professionals did not take into account the influence of the internal structure and ignored the heat sink of the structure, resulting in a high thermal load input;

[0004] 2) The calculation error is accumulated and repeated load mapping error results in poor accuracy of calculation results;

[0005] 3) The entire calculation process is completed by different professionals, including aerodynamics, structure, and strength. The models and grids are not unified, and the collaborative efficiency is low.

[0006] This application is proposed in view of the above-mentioned technical defects. Summary of the invention

[0007] The purpose of the present application is to provide a fluid-thermal-solid coupling analysis method for an aircraft body structure to overcome or alleviate at least one of the known technical deficiencies.

[0008] The technical solution of this application is:

[0009] A method for fluid-thermal-solid coupling analysis of an aircraft body structure, comprising:

[0010] Step 1: Establish the geometric model of the body structure;

[0011] Step 2: Perform aerodynamic meshing on the airframe structure geometry model, and complete structural meshing simultaneously during the process of establishing the external thermal flow field of the airframe structure;

[0012] Step 3: Perform flow field analysis on the airframe structure, and complete external temperature field analysis and internal heat transfer analysis based on the external thermal flow field boundary conditions;

[0013] Step 4: Perform separate structural meshing on the airframe structure geometry model and map the flow field analysis thermal load onto the structural mesh;

[0014] Step 5: Conduct force field analysis on the aircraft structure, including static analysis, vibration characteristic analysis, and modal analysis.

[0015] According to at least one embodiment of the present application, in the above-mentioned method for fluid-thermal-solid coupling analysis of aircraft fuselage structure, in step one, a geometric model of the fuselage structure is established using CATIA.

[0016] According to at least one embodiment of the present application, in the above-mentioned aircraft vehicle body structure fluid-thermal-solid coupling analysis method, in step two, the body structure geometric model is aerodynamically meshed using ICEM, the external thermal flow field of the body structure is established, and structural meshing is performed.

[0017] According to at least one embodiment of the present application, in the above-mentioned aircraft vehicle body structure fluid-thermal-solid coupling analysis method, in step three, FLUENT is used to perform flow field analysis on the body structure, and the external thermal flow field of the body structure is used as a boundary condition to complete external temperature field analysis and internal heat transfer analysis to obtain thermal load.

[0018] According to at least one embodiment of the present application, in the above-mentioned aircraft vehicle body structure fluid-thermal-solid coupling analysis method, in step four, the body structure geometric model is divided into a separate structural grid using Hyperworks, and then the flow field analysis thermal load is mapped to the structural grid.

[0019] According to at least one embodiment of the present application, in the above-mentioned method for fluid-thermal-solid coupling analysis of aircraft fuselage structure, in step five, static analysis and vibration characteristic analysis of the fuselage structure are performed using Workbench, and modal analysis of the fuselage structure is performed using the MODAL tool.

[0020] This application has at least the following beneficial technical effects:

[0021] A method for flow-heat-solid coupling analysis of aircraft body structure is provided. The design uses a set of models to complete the flow-heat-solid multi-field coupling analysis. The flow field calculation process takes the influence of the internal structure into consideration, and the structural force field analysis calls the flow field analysis results in situ. This can fundamentally avoid the human errors caused by repeated load mapping and the high thermal load problem caused by incomplete model considerations, while improving the collaborative efficiency of the calculation. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 is a schematic diagram of a fluid-thermal-solid coupling analysis method for an aircraft body structure provided in an embodiment of the present application;

[0023] Figure 2 is a schematic diagram of aerodynamic meshing of a body structure geometric model provided in an embodiment of the present application;

[0024] Figure 3 It is a schematic diagram of flow field analysis of a body structure and external temperature field distribution provided in an embodiment of the present application;

[0025] Figure 4 It is a schematic diagram of flow field analysis and temperature streamline distribution of a machine body structure provided in an embodiment of the present application;

[0026] Figure 5 It is a schematic diagram of force field analysis of a body structure and structural stress distribution provided in an embodiment of the present application;

[0027] Figure 6 It is a schematic diagram of force field analysis of a body structure and structural deformation distribution provided in an embodiment of the present application;

[0028] Figure 7 It is a schematic diagram of force field analysis and structural modal analysis of the body structure provided in an embodiment of the present application.

[0029] In order to better illustrate the present embodiment, some contents of the drawings may be omitted, enlarged or reduced, which is only used for illustrative purposes and should not be construed as limiting the present application. DETAILED DESCRIPTION

[0030] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0031] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should be the common meanings understood by those skilled in the art in the field to which this application belongs. The term "include" used in the description of this application means that the concepts appearing before the term include the concepts listed after the term and their equivalents, without excluding other related concepts.

[0032] A method for fluid-thermal-solid coupling analysis of aircraft body structures, such as Figure 1 shown.

[0033] Step 1: Establish the geometric model of the body structure.

[0034] Specifically, CATIA can be used to establish the body structure geometric model.

[0035] Step 2: Perform aerodynamic meshing on the airframe structure geometry model, and complete the structural meshing simultaneously during the process of establishing the external thermal flow field of the airframe structure.

[0036] Specifically, ICEM can be used to perform aerodynamic meshing on the airframe structure geometric model, establish the external thermal flow field of the airframe structure, and perform structural meshing.

[0037] Step 3: Perform flow field analysis on the body structure, and complete external temperature field analysis and internal heat transfer analysis based on external thermal flow field boundary conditions.

[0038] Specifically, FLUENT can be used to perform flow field analysis on the airframe structure, and the external thermal flow field of the airframe structure can be used as the boundary condition to complete the external temperature field analysis and internal heat transfer analysis to obtain the thermal load.

[0039] Step 4: Divide the airframe structure geometry model into a separate structural grid and map the flow field analysis thermal load onto the structural grid.

[0040] Specifically, Hyperworks can be used to divide the body structure geometry model into a separate structural grid. This structural grid is a surface grid, which is different from the solid grid used for flow field analysis. The thermal load of the flow field analysis is then mapped to the structural grid.

[0041] Step 5: Conduct force field analysis on the aircraft structure, including static analysis, vibration characteristic analysis, and modal analysis.

[0042] Specifically, Workbench can be used to perform static analysis and vibration characteristics analysis on the airframe structure, and the MODAL tool can be used to perform modal analysis on the airframe structure.

[0043] The above-mentioned embodiment discloses an aviation vehicle body structure flow-heat-solid coupling analysis method, which is designed to complete the flow-heat-solid multi-field coupling analysis through a set of models. The flow field calculation process takes into account the influence of the internal structure, and the structural force field analysis calls the flow field analysis results in situ. This can fundamentally avoid the human errors caused by repeated load mapping, avoid the problem of high thermal loads caused by incomplete model considerations, and at the same time improve the collaborative efficiency of the calculation.

[0044] In a specific example, the flow-thermal-solid coupling analysis method for the aircraft body structure disclosed in the above embodiment is used to perform calculations and analysis on a simplified aircraft structure. The flow field inlet boundary is selected as a mass inlet of 0.5 kg / s and a temperature of 300 K. The outlet is selected as the outflow boundary condition. In the force field analysis, the inlet boundary is taken as the fixed support constraint condition, and the flow field analysis result is taken as the thermal boundary condition.

[0045] Perform aerodynamic meshing on the airframe structure geometry model, such as Figure 2 shown.

[0046] The flow field analysis of the airframe structure, the external temperature field and its streamline distribution are as follows: Figure 3 , Figure 4 shown.

[0047] Force field analysis is performed on the aircraft structure, and the structural stress and deformation distribution are as follows: Figure 5 , Figure 6 As shown, the structural modes are Figure 7 shown.

[0048] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. A method for fluid-thermal-solid coupling analysis of aircraft body structure, characterized in that: include: Step 1: Establish the geometric model of the body structure; Step 2: Perform aerodynamic meshing on the airframe structure geometry model, and complete structural meshing simultaneously during the process of establishing the external thermal flow field of the airframe structure; Step 3: Perform flow field analysis on the airframe structure, and complete external temperature field analysis and internal heat transfer analysis based on the external thermal flow field boundary conditions; Step 4: Perform separate structural meshing on the airframe structure geometry model and map the flow field analysis thermal load onto the structural mesh; Step 5: Conduct force field analysis on the aircraft structure, including static analysis, vibration characteristic analysis, and modal analysis.

2. The method for fluid-thermal-solid coupling analysis of aircraft body structure according to claim 1, characterized in that: In step 1, the body structure geometric model is established using CATIA.

3. The method for fluid-thermal-solid coupling analysis of aircraft body structure according to claim 2, characterized in that: In step 2, ICEM is used to perform aerodynamic meshing on the airframe structure geometry model, establish the external thermal flow field of the airframe structure, and perform structural meshing.

4. The method for fluid-thermal-solid coupling analysis of aircraft body structure according to claim 3, characterized in that: In step three, FLUENT is used to perform flow field analysis on the airframe structure, and the external thermal flow field of the airframe structure is used as the boundary condition to complete the external temperature field analysis and internal heat transfer analysis to obtain the thermal load.

5. The method for fluid-thermal-solid coupling analysis of aircraft body structure according to claim 4, characterized in that: In step 4, Hyperworks is used to divide the airframe structure geometry model into separate structural grids, and then the flow field analysis thermal load is mapped to the structural grid.

6. The method for fluid-thermal-solid coupling analysis of aircraft body structure according to claim 5, characterized in that: In step five, static analysis and vibration characteristic analysis of the airframe structure are performed using Workbench, and modal analysis of the airframe structure is performed using the MODAL tool.

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