Simulating Crack Propagation of a Selected Structural Component of the PZL-130 Orlik TC-II Aircrafts

Q4 Engineering

Fatigue of Aircraft Structures Pub Date : 2014-06-01 DOI:10.1515/fas-2014-0013

Krzysztof Jankowski, P. Reymer

引用次数: 2

Abstract

Abstract This paper presents the process of estimating crack propagation within a selected structural component of the PZL-130 Orlik TC-II using a numerical model. The model is based on technical drawings and measurements of the real structure. The proper definition of the geometry, including the location and size of the gap between elements, is significant for mesh generation. During the simulation process the gap is combined node by node. Each time, the strain energy release rate (G) is calculated. The stress intensity factor and geometry correction factor are defined for consecutive crack lengths, and used further on to estimate crack propagation.

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PZL-130 Orlik TC-II飞机结构部件裂纹扩展模拟

摘要本文介绍了用数值模型估计PZL-130 Orlik TC-II结构构件内裂纹扩展的过程。该模型是根据实际结构的技术图纸和测量结果建立的。适当的几何定义，包括元素之间间隙的位置和大小，对网格生成非常重要。在模拟过程中，间隙是一个节点一个节点地组合。每次计算应变能释放率(G)。定义了连续裂纹长度的应力强度因子和几何修正因子，并进一步用于估计裂纹扩展。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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来源期刊

Fatigue of Aircraft Structures Engineering-Safety, Risk, Reliability and Quality

CiteScore

0.40

自引率

0.00%

发文量

期刊介绍： The publication focuses on problems of aeronautical fatigue and structural integrity. The preferred topics include: full-scale fatigue testing of aircraft and aircraft structural components, fatigue of materials and structures, advanced materials and innovative structural concepts, damage tolerant design of aircraft structure, life extension and management of ageing fleets, structural health monitoring and loads, fatigue crack growth and life prediction methods, NDT inspections, airworthiness considerations.