Recent developments on damage modeling and finite element analysis for composite laminates: A review

Review: Computational methods for bird strike simulations: A review

Damage characterization of laminated composites has been thoroughly studied the last decades where researchers developed several damage models, and in combination with experimental evidence, contributed to better understanding of the structural behavior of these structures. Experimental techniques played an essential role on this progress and among the techniques that were utilized, acoustic emission (AE) was extensively used due to its advantages for in-situ damage monitoring with high sensitivity and its capability to inspect continuously a relatively large area. This paper presents a comprehensive review on the use of AE for damage characterization in laminated composites. The review is divided into two sections; the first section discusses the literature for damage diagnostics and it is presented in three subsections: damage initiation detection, damage type identification and damage localization, while the second section is devoted to damage prognostics and it focuses on the remaining useful life (RUL) and residual strength prediction of composite structures using AE data. In every section, efforts have been made to analyze the most relevant literature, discuss in a critical manner the results and conclusions, and identify possibilities for future work.

Damage characterization of laminated composites using acoustic emission: A review

An improved peridynamic approach for quasi-static elastic deformation and brittle fracture analysis

Advances, limitations and prospects of nondestructive testing and evaluation of thick composites and sandwich structures: A state-of-the-art review

Implementation of the virtual crack closure technique in engineering FE calculations

In situ Barely Visible Impact Damage detection and localization for composite structures using surface mounted and embedded PZT transducers: A comparative study

The advantages of FML structures (e.g. GLARE or CARAL) come from the improvement in durability of such struc" tures, however, in such structures failure modes may also occur. Failure modes which may occur in such structures are simi" lar to those in epoxy composites but some of them are associated with fracture mechanics similar to e.g. aluminium alloys. The quality control of materials and structures in aircraft is an important issue, also for FML laminates. For FML parts, a 100% non"destructive inspection for internal quality during the manufacturing process is required. In the case of FML composites, the most significant defects that should be detected by non"destructive testing are porosity, delaminations and cracks. In this paper, the use of non"destructive different methods for the inspection of Fibre Metal Laminates was presented. The novelty in the approach will include the use of multimode and highly specialized inspection methods such as: ultrasonics, thermography, air"coupled ultrasonics, and X"ray tomography.

Inspection methods for quality control of fibre metal laminates (FML) in aerospace components

Fatigue life estimation and crack propagation description are the most important components in the analysis of life span of structural components but it may require time and expense to investigate it experimentally. For fatigue crack propagation studying in cases when it is difficult to obtain detailed results by direct experimentation computer simulation is especially useful. Hence, to be efficient, the crack propagation and durability of construction or structural component software should estimate the remaining life both experimentally and by simulation. The critical size of the crack or critical component load can be calculated using material constants which have been derived experimentally and from the constant amplitude crack propagation curve, crack size-life data and curve using crack propagation software. Many works in the field of fracture mechanics prove significant development in the numerical analysis of test data from fatigue crack propagation tests.

/pdf/good-practice-for-fatigue-crack-growth-curves-description-2ia6jna3p4.pdf

Good Practice for Fatigue Crack Growth Curves Description

Abstract This article presents a concept of the full scale fatigue test of a Su-22 fighter bomber. The authors define the general concept and goals of the test as well as the tasks to be accomplished in the preparation stage. The current work status is summarized and future tasks are defined.

/pdf/the-concept-of-a-full-scale-fatigue-test-of-a-su-22-fighter-5ddgwkqsdy.pdf

Andrzej Leski

Papers

Implementation of the virtual crack closure technique in engineering FE calculations

In situ Barely Visible Impact Damage detection and localization for composite structures using surface mounted and embedded PZT transducers: A comparative study

Inspection methods for quality control of fibre metal laminates (FML) in aerospace components

Good Practice for Fatigue Crack Growth Curves Description

The Concept of a Full Scale Fatigue Test of a Su-22 Fighter Bomber