Motion airfoil strength analysis simplification method based on finite element model

Abstract

The invention belongs to the field of aviation structure strength analysis, and particularly relates to a finite element model-based motion airfoil strength analysis simplification method. Comprising the following steps: S1, acquiring a total airfoil motion process, and dispersing the total airfoil motion process into n static calculation points; s2, establishing an airfoil motion static working condition model, and determining a model boundary; s3, inputting the airfoil angles, the loads and the boundary displacements of all the static calculation points as conditions of static analysis models to obtain n static analysis models; s4, calculating n static analysis models to obtain target parameters of the moving airfoil under all static calculation points; and S5, judging whether the target parameters under all the static calculation points meet the static strength requirement or not. The method reduces analysis steps, shortens the working process and improves the working efficiency.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of aviation structure strength analysis, and particularly relates to a simplified method for strength analysis of a moving airfoil based on a finite element model. BACKGROUND

[0002] During the movement of the airfoil, when the angle change frequency is low, the load cannot cause structural dynamic response or can cause very small dynamic response. The conventional analysis method is complicated in steps and low in efficiency. SUMMARY

[0003] To solve the above problems, the application provides a simplified method for strength analysis of a moving airfoil based on a finite element model, which comprises the following steps:

[0004] Step S1: obtaining a total movement course of the airfoil, and discretizing the total movement course of the airfoil into n static calculation points;

[0005] Step S2: establishing an airfoil movement static force working condition model, and determining a model boundary;

[0006] Step S3: inputting the airfoil angle, load and boundary displacement of all the static calculation points as condition inputs of a static analysis model, and obtaining n static analysis models;

[0007] Step S4: calculating the n static analysis models, and obtaining target parameters of the moving airfoil under all the static calculation points;

[0008] Step S5: judging whether the target parameters under all the static calculation points meet static strength requirements.

[0009] Preferably, the total time of the total movement course of the airfoil is obtained, the total time is discretized into n time points, and the airfoil movement static corresponding to each time point is taken as each static calculation point.

[0010] Preferably, the total angle of the total movement course of the airfoil is obtained, the total angle is discretized into n transient points, and the airfoil movement static corresponding to each transient point is taken as each static calculation point.

[0011] Preferably, the model boundary comprises a suspension support ear hole center and a control actuator front point of the airfoil.

[0012] Preferably, the n static analysis models are solved in batches by a finite element analysis calculation software.

[0013] Preferably, the target parameters comprise deformation, stress and strain.

[0014] Preferably, the target parameter is established with n discrete points of static calculation points, the curve of the target parameter and the total motion of the airfoil is obtained by interpolation method, and whether the target parameter meets the static strength requirement in the total motion of the airfoil is determined according to the curve.

[0015] The advantages of the present application include: the load does not cause dynamic response or causes very small dynamic response relative to the airfoil with low angle change frequency. Therefore, a simplified method for analyzing the strength of the moving airfoil based on the finite element model is provided, the total motion of the airfoil is discretized into n static time points, and whether the deformation, stress and strain of the moving airfoil under n static working conditions meet the static strength requirement is analyzed. The method reduces the analysis steps, shortens the work flow and improves the work efficiency. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 is a schematic diagram of the total motion of the airfoil in a preferred embodiment of the present application. DETAILED DESCRIPTION

[0017] In order to make the technical solutions of the present application and the advantages thereof clearer, the technical solutions of the present application will be further clearly and completely described in detail below in combination with the drawings. It should be understood that the specific embodiments described herein are only part of the embodiments of the present application, and are only used to explain the present application, but not to limit the present application. It should be noted that, for the purpose of description, only parts related to the present application are shown in the drawings, and other related parts can be referred to the usual design. In the case of no conflict, the embodiments in the present application and the technical features in the embodiments can be combined to obtain new embodiments.

[0018] In addition, it should be noted that, unless otherwise explicitly specified and limited, the terms "mounting", "connection", "connection" and the like used in the description of the present application should be understood in a broad sense, for example, the connection can be fixed connection, or detachable connection, or integrally connected; can be mechanical connection, or electrical connection; can be directly connected, or indirectly connected through intermediate medium, or the internal communication of two elements, and those skilled in the art can understand the specific meaning of the terms in the present application according to the specific circumstances.

[0019] As shown in Figure 1 ,

[0020] Step one, discretize the total motion process into 30 static calculation points according to the angle change frequency 1 。 ~30 。 s, the total motion process is discretized into 30 static calculation points according to the angle change frequency 1 。 / s, △t=1s, any static calculation point t i is defined as t i =is(i=1,2,…,30);

[0021] Step two, determine the wing surface analysis model boundary, the model boundary is the center of the suspension support ear hole and the front point of the control actuator;

[0022] Step three, define 30 static force working conditions, wherein, the static calculation point t i The wing surface angle, load, and boundary displacement are respectively input as the model angle, load, and boundary condition of the i-th static force working condition;

[0023] Step four, use the finite element analysis calculation software to batch calculate the deformation, stress, and strain of the moving wing surface under the 30 static force working conditions, and analyze whether the deformation, stress, and strain meet the static strength requirements.

[0024] The above is only a specific embodiment of the present application, but the protection scope of the present application is not limited to this. Any person skilled in the art can easily think of changes or replacements within the technical range disclosed in the present application, which should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A simplified method for analyzing the strength of a moving airfoil based on a finite element model, characterized by, The application relates to a method for calculating the static strength of a moving wing surface, comprising the following steps: Step S1: acquiring the total motion course of the wing surface, and discretizing the total motion course of the wing surface into n static calculation points; Step S2: establishing a wing surface motion static force working condition model, and determining the model boundary; Step S3: inputting the wing surface angle, load and boundary displacement of all the static calculation points into the static analysis model as the condition, and obtaining n static analysis models; Step S4: calculating the n static analysis models, and obtaining the target parameters of the moving wing surface under all the static calculation points; Step S5: judging whether the target parameters under all the static calculation points meet the static strength requirement.

2. The simplified method for strength analysis of a finite element model motion airfoil surface according to claim 1, wherein, The total time of the total motion course of the wing surface is acquired, the total time is discretized into n time points, and the wing surface motion static corresponding to each time point is taken as each static calculation point.

3. The simplified method for strength analysis of a moving airfoil based on a finite element model according to claim 1, wherein The total angle of the total motion course of the wing surface is acquired, the total angle is discretized into n transient points, and the wing surface motion static corresponding to each transient point is taken as each static calculation point.

4. The simplified method for strength analysis of a moving airfoil based on a finite element model according to claim 1, wherein The model boundary comprises a hanging support ear hole center of the wing surface and a front point of a control actuator.

5. The simplified method for strength analysis of a moving airfoil based on a finite element model according to claim 1, wherein The n static analysis models are solved in batches by using a finite element analysis calculation software.

6. The simplified method for strength analysis of a moving airfoil based on a finite element model according to claim 1, wherein The target parameters comprise deformation, stress and strain.

7. The simplified method for strength analysis of a moving airfoil based on a finite element model according to claim 1, wherein A discrete point graph of the target parameters and the n static calculation points is established, a curve graph of the target parameters and the total motion course of the wing surface is obtained by using an interpolation method, and whether the target parameters meet the static strength requirement in the total motion course of the wing surface is judged according to the curve graph.

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