Optimization design method for large-deformation flexible sealing structure

Abstract

The invention belongs to the technical field of electric data processing, and particularly relates to a large-deformation flexible sealing structure optimization design method which comprises the steps that a finite element analysis model is established, and the finite element analysis model comprises a sealing structure, a fixed connection structure and a control surface skin; one end of the sealing structure is fixed on the fixed connecting structure, and the other end is lapped with the control surface skin; creating a motion working condition for the finite element analysis model, applying an aerodynamic load, and obtaining a position where the contact force between the sealing structure and the control surface skin is maximum; taking the condition that the contact force of the sealing structure at the position with the maximum contact force and the control surface skin is not greater than a set value as a constraint, and taking the minimum strain of the sealing structure as a target to obtain design parameters of the sealing structure; and selecting the material and the shape of the sealing structure according to the design parameters.

Description

Technical Field

[0001] The present application belongs to the technical field of electrical data processing, and in particular relates to an optimization design method for a large deformation flexible sealing structure. Background Art

[0002] Due to aerodynamic and functional requirements, more and more aircraft are now equipped with flexible sealing structures between the moving wing surface and the fixed structure. When designing a flexible sealing structure, the most prominent contradiction is that it must have sufficient rigidity to resist the super-strong aerodynamic suction, and a certain flexibility to follow the deflection of the moving wing surface to produce large deformation without damage, and it must also take into account the continuity and integrity of the full-span wing profile in the cruise configuration. Domestic research on flexible sealing structures is in its infancy, and there is a lack of forward design capabilities for the design of such high-rigidity, large-deformation flexible sealing structures. The following key issues need to be urgently resolved during the development process: 1) The design method is immature, mainly because the structural parameters cannot be determined by the forward design method, the iteration efficiency is low, the development cycle is long, and the cost is high; 2) The structural rigidity is small, the deformation is large when loaded, and the sealing function does not meet the requirements; 3) The friction between the flexible sealing structure and the moving wing surface is large, which is easy to damage the moving wing surface structure. Summary of the invention

[0003] In order to solve the above problems, the present application provides a method for optimizing the design of a large deformation flexible sealing structure, including:

[0004] Establishing a finite element analysis model, the finite element analysis model includes: a sealing structure, a fixed connection structure and a rudder surface skin; one end of the sealing structure is fixed to the fixed connection structure, and the other end is overlapped with the rudder surface skin;

[0005] Create motion conditions for the finite element analysis model and apply aerodynamic loads to obtain the position where the contact force between the sealing structure and the rudder skin is the largest;

[0006] Taking the contact force between the sealing structure and the rudder surface skin at the position where the contact force is the largest as a constraint that the contact force is not greater than a set value and taking the minimum strain of the sealing structure as a goal, the design parameters of the sealing structure are obtained;

[0007] The material and shape of the sealing structure are selected according to the design parameters.

[0008] Preferably, the sealing structure is in the form of a cantilever beam with a variable cross-section in the chord direction and a certain pre-deformation.

[0009] Preferably, the sealing structure is formed by composite material plies.

[0010] Preferably, the design parameters include preset deformation, chord-wise section, partition width and partition thickness.

[0011] Preferably, the ply ratio of the isotropic fabric and the unidirectional tape is determined based on the chord-wise cross section and the partition thickness, and the ply ratio of the sealing structure composite material is finally determined based on the ply ratio.

[0012] Preferably, the sealing structure is fixedly mounted on the fixed connection structure by means of screws.

[0013] Preferably, based on the finite element analysis model of the design parameters, the optimal screw arrangement is obtained by comparative analysis of arrangements of different nail spacings and different numbers of nail rows.

[0014] Preferably, it further includes: obtaining a position where the contact force between the sealing structure and the rudder surface skin is the smallest; the constraint also includes: the contact force between the sealing structure and the rudder surface skin at the position where the contact force is the smallest is not less than a critical value.

[0015] Preferably, it further includes: the partitions of the partition width and the partition thickness respectively include: an installation area connected to the fixed connection structure, a transition area and a rudder surface overlapping area overlapped with the rudder surface skin.

[0016] Advantages of this application include:

[0017] 1. Achieved a balance between high stiffness and large deformation of structural materials;

[0018] 2. The stress analysis of the whole process of sealing structure assembly and deflection is realized;

[0019] 3. Explore the optimization method of large deformation flexible sealing structure with multiple variables and multiple constraints;

[0020] 4. The design process and design criteria are solidified, and an optimization design method for anisotropic large deformation flexible sealing structures is proposed, which improves the mechanical properties of this type of sealing structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a flow chart of a method for optimizing the design of a large deformation flexible sealing structure according to a preferred embodiment of the present application. DETAILED DESCRIPTION

[0022] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be further described in detail in detail and in detail in conjunction with 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. In the absence of conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0023] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installed", "connected", "connected" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or the internal connection of two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0024] like Figure 1 As shown: The optimization design method of the large deformation flexible sealing structure of the present application includes:

[0025] 1. Design the installation layout of the sealing structure based on the relative position of the fixed connection structure and the rudder surface deflection.

[0026] The sealing structure is a cantilever beam with variable cross-section in the chord direction and a certain pre-deformation. According to the relative position of the fixed connection structure and the rudder surface and the cantilever beam theory, a preliminary model of the sealing structure is established.

[0027] 2. Establish finite element analysis model and motion conditions.

[0028] A finite element model is established based on the preliminary model of the sealing structure, and the finite element model includes a fixed connection structure, a sealing structure, and a rudder skin. The sealing structure is divided into an installation area, a transition area, and a rudder overlap area. The installation area and the fixed connection structure are contact pairs and are connected by bolts. The rudder overlap area creates a contact relationship with the rudder skin, and the contact relationship is overlap.

[0029] Create assembly and deflection conditions in the finite element model to simulate the actual installation and deflection process of the sealing structure, and apply aerodynamic loads at the same time.

[0030] 3. Analyze the deformation and load-bearing requirements of the sealing structure, conduct multi-parameter comprehensive optimization, and design the composite material laying scheme for the sealing structure.

[0031] Under the condition of ensuring the sealing function of the sealing structure, it includes: obtaining the position where the contact force between the sealing structure and the rudder surface skin is the largest and obtaining the position where the contact force between the sealing structure and the rudder surface skin is the smallest; making the maximum contact force smaller than a set value, reducing the pressure on the rudder surface skin, reducing structural wear, making the maximum minimum contact force smaller than another set value, and avoiding separation of the sealing structure from the rudder surface skin;

[0032] Then, multi-parameter shape optimization is performed with the goal of minimizing strain to obtain parameters such as preset deformation of the sealing structure, chordal section, and partition width and thickness. In another embodiment, an optimization goal of minimizing weight can be added, and a dual-objective optimization method can be used for optimization.

[0033] Obtain optimized parameters such as chord-wise cross-section and partition thickness, carry out optimal design of ply plan, and determine the ratio of isotropic fabric and unidirectional tape;

[0034] Based on the layup ratio and taking into account the manufacturing processability of the composite material, the composite layup plan for the sealing structure is finally determined;

[0035] 4. Optimization of sealing structure connection area.

[0036] Based on the optimized and adjusted sealing structure model, the structural assembly connection design of the sealing structure connection area is optimized. Through comparative analysis of arrangements with different nail spacings and different numbers of nails, the optimal screw arrangement is obtained.

[0037] 5. Complete the strength check of sealing structures and connections.

[0038] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A method for optimizing the design of a large deformation flexible sealing structure, characterized in that: include: Establishing a finite element analysis model, the finite element analysis model includes: a sealing structure, a fixed connection structure and a rudder surface skin; one end of the sealing structure is fixed to the fixed connection structure, and the other end is overlapped with the rudder surface skin; Create motion conditions for the finite element analysis model and apply aerodynamic loads to obtain the position where the contact force between the sealing structure and the rudder skin is the largest; Taking the contact force between the sealing structure and the rudder surface skin at the position where the contact force is the largest as a constraint that the contact force is not greater than a set value and taking the minimum strain of the sealing structure as a goal, the design parameters of the sealing structure are obtained; The material and shape of the sealing structure are selected according to the design parameters.

2. The optimization design method for a large deformation flexible sealing structure according to claim 1, characterized in that: The sealing structure adopts a cantilever beam with a variable cross-section in the chord direction and a certain pre-deformation.

3. The optimization design method for a large deformation flexible sealing structure according to claim 2, characterized in that: The sealing structure is formed by composite material plywork.

4. The optimization design method for a large deformation flexible sealing structure according to claim 3, characterized in that: The design parameters include preset deformation, chordal section, partition width and partition thickness.

5. The optimization design method for a large deformation flexible sealing structure according to claim 4, characterized in that: The ply ratio of the isotropic fabric and the unidirectional tape is determined based on the chord-wise cross section and the partition thickness, and a ply scheme of the sealing structure composite material is finally determined based on the ply ratio.

6. The optimization design method for a large deformation flexible sealing structure according to claim 5, characterized in that: The sealing structure is fixedly mounted on the fixed connection structure by means of screws.

7. The optimization design method for a large deformation flexible sealing structure according to claim 6, characterized in that: Based on the finite element analysis model of the design parameters, the optimal screw arrangement is obtained through comparative analysis of arrangements of different nail spacings and different numbers of nail rows.

8. The optimization design method for a large deformation flexible sealing structure according to claim 1, characterized in that: Also includes: Obtain the position where the contact force between the sealing structure and the rudder surface skin is the smallest; The constraint also includes: the contact force between the sealing structure and the rudder surface skin at the position where the contact force is the smallest is not less than a critical value.

9. The optimization design method for a large deformation flexible sealing structure according to claim 1, characterized in that: Also includes: The partitions of the partition width and the partition thickness respectively include: an installation area connected to the fixed connection structure, a transition area, and a rudder surface overlapping area overlapped with the rudder surface skin.

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