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Fatigue system reliability analysis method for composite material laminated structure

A composite material layer and analysis method technology, which is applied in the field of fatigue reliability analysis of composite material laminated structures, can solve problems such as no longer applicable, and achieve the effect of improving rationality

Active Publication Date: 2020-01-17
BEIHANG UNIV
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Problems solved by technology

Traditional structural fatigue reliability analysis and solution methods are no longer applicable

Method used

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  • Fatigue system reliability analysis method for composite material laminated structure
  • Fatigue system reliability analysis method for composite material laminated structure
  • Fatigue system reliability analysis method for composite material laminated structure

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Embodiment Construction

[0033] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0034] Such as figure 1 As shown, the present invention proposes a fatigue system reliability analysis method of a composite material laminated structure, comprising the following steps:

[0035] (1) According to the material properties of the laminate structure: the stiffness parameter M i with the intensity parameter Q j , i=1,2,3,...,m, j=1,2,3,...,n, m represents the total number of stiffness parameters, n represents the total number of strength parameters;

[0036] Combined with the failure criterion of composite single-layer plate, that is, the limit state equation, the two-dimensional Hashin strength criterion widely used in composite material structure design and failure analysis is selected. This criterion describes in detail the failure criteria corresponding to different failure modes:

[0037] Fiber Tensile Failure:

[0038] F...

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Abstract

The invention discloses a fatigue system reliability analysis method of a composite material laminated structure. According to the method, under the action of a fatigue load and a given constraint condition, multiple failure modes of the structure and correlation of the failure modes are fully considered, so that system reliability analysis is carried out. The method comprises the following steps:firstly, calculating the failure probability of each failure element in different failure modes by combining a two-dimensional Hashin criterion according to specific characteristics of laminated plate structure materials, loads and the like, and considering that a layer with the maximum failure probability is damaged; secondly, according to the built one-way laminated plate degradation model, degrading material attributes in the fatigue loading process, subjecting the degraded model to reanalysis, calculating the failure probability of each failure element, and determining a main failure path; and finally, checking the residual strength of the structure after cyclic loading is finished, establishing a fatigue system reliability index on the basis, and providing guidance and reference forsubsequent analysis and optimization.

Description

technical field [0001] The invention relates to the technical field of fatigue reliability analysis of composite material laminated structures, in particular to the reasonable characterization of the reliability of the fatigue system of laminated structures by considering multiple failure modes under the condition of given cycle number and load spectrum. The establishment and formulation of an accurate solution method for system reliability. Background technique [0002] With its superior mechanical properties, composite materials have become a hot topic of research by scholars at home and abroad. For the typical structure of composite materials, laminates are widely used in various aspects such as aviation, aerospace, ships, and medical treatment. The depth and breadth of composite material technology research has reached It has become an important benchmark for the development of national science and technology. Therefore, the research on the mechanical characteristics ana...

Claims

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Application Information

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IPC IPC(8): G06F30/23G06F30/17G06F30/28
Inventor 王晓军倪博文王磊马雨嘉任强
Owner BEIHANG UNIV
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