<abstract xmlns="http://www.w3.org/1999/xhtml">From the safety point of view, one of the most important issues regarding aircraft operations is ensuring the durability of the structural components. Corrosion processes can have a significant effect on the integrity of structural materials and are usually associated with aircraft aging. Due to the variety of materials used, environments and loads impacting the planes, a wide range of different types of corrosion may occur in aircraft structures. The main aim of this study is to present some theoretical knowledge related to corrosion processes as well as problems of aircraft structures associated with corrosion occurrence. Firstly, the paper presents a brief overview of what corrosion is and what different types of corrosion are. Secondly, some selected aircraft failures caused by corrosion are shortly presented and discussed.</abstract>

Aircraft Corrosion – Review of Corrosion Processes and its Effects in Selected Cases

<abstract xmlns="http://www.w3.org/1999/xhtml">Damage tolerance of composite aircraft structure is one of the main areas of research, important when a new product is being developed. There are a number of variables, such as damage characteristics (dent depth, delamination area) and loading parameters (load type, amplitude of cyclic loading, load sequence) that need to be investigated experimentally [1]. These tests of composite materials are usually performed at an element level and are carried out in order to validate the analytical model, developed to predict the full-scale component’s behaviour. The paper presents the results of compression testing of the [36/55/9] carbon fibre/epoxy laminate, manufactured with the Automated Fibre Placement technology (AFP) and subjected to static and fatigue loads. The laminate compression loading mode was achieved through sandwich 4-point flexure. At the stage of fatigue testing, two parameters were investigated: the damage size, simulated by the hole diameter and the fatigue load level. Based on the test results, the laminate fatigue load limit equal to 75% of the OHC failure load was evaluated. By collating the static and fatigue tests results, the damage tolerance characteristic of the considered laminate was created.</abstract>

Influence of the Fatigue Load Level and the Hole Diameter on the Laminate Structure’s Fatigue Performance

<abstract xmlns="http://www.w3.org/1999/xhtml">The paper presents the results of diffraction stress measurement in Al/SiC composite and in 2124T6 aluminum alloy during the in situ tensile test. The main aim of the work is to observe the stress values for different stages of tensile test for the composite after applying two types of thermal treatment and for the alloy used as a matrix in this composite, to identify the type of hardening process. The experimental results were compared against the calculations results obtained from the self-consistent model developed by Baczmański [1] - [3] to gain the information about the micromechanical properties (critical resolved shear stress τcr and hardening parameter H) of the examined materials. This comparison allowed researchers to determine the role of reinforcement in the composite as well as the impact of the heat treatment on the hardening of the material.</abstract>

The Hardening in Alloys and Composites and Its Examination with a Diffraction and Self-Consistent Model

<abstract xmlns="http://www.w3.org/1999/xhtml">Computed tomography (CT) of aluminum welded joint specimen has been performed. On the tomographic cross sections some defects have been found. To verify them the metallography cross sections of welded has been done. It was found that selected defects are micro cracks.</abstract>

Verification of the Computed Tomography Results of Aluminum Alloy Welded Joint

<abstract xmlns="http://www.w3.org/1999/xhtml">The cable flight control systems are commonly used for the control of small airplanes. In these systems, the cables are the only elements transmitting loads from the pilot to the control surfaces. During a flight the cables are moving through pulleys and are subjected to variable loads. A simple analysis of stress in the cable shows that the stress generated by the cyclical bending on the pulleys causes the fatigue of the wires.This phenomenon was noticed on a military aircraft of the M28 family during periodic maintenance inspection in 2007. The endurance tests of KSAN cables of the diameter equal to 3.5 mm and 1.8 mm were performed at the PZL MIELEC. The tests showed the limited fatigue life of the cables due to a progressive increase in the number of broken wires.</abstract>

The Fatigue Life of Cables in Aircraft Flight Control Systems

<abstract xmlns="http://www.w3.org/1999/xhtml">Rivets are critical areas in metal airframes from the fatigue point of view. Fatigue behaviour of riveted joints depends strongly on the residual stress system around the rivet holes. The both most convenient and most common method of determining these stresses is the Finite Element (FE) analyses. The validation of models used is necessary to ensure the reliability of results.This paper presents the validation process of the riveting FE simulations for the universal and the countersunk rivets. At first, the material model of the rivets was validated with the use of the force–displacement curves of the press stamp obtained experimentally. Because of the displacement measurement method, it was necessary to take into account the flexibility of the stand. After that, good correlation between the numerical simulations and the experiment was obtained for both rivet types.At the second stage, strains around driven heads measured with the use of strip gauge patterns were compared with the results of the FE simulations. Quite good correlation was obtained for the countersunk rivet. In the case of the universal rivet, the numerical results are significantly higher values than the measured ones. Differences in correlation of the experiments and FE simulations for the analysed rivet types probably result from material differences of the rivets.</abstract>

Experimental Validation of Riveting Process Fe Simulation

<abstract xmlns="http://www.w3.org/1999/xhtml">The paper presents a summary of non-destructive testing and evaluation (NDT&amp;E) methods applied in inspections of structural aircraft components. This brief review covers the most commonly applied methods such as visual and penetrant inspections, tap-testing, eddy current inspections, shearography, thermography, acoustic emission testing, radiographic and tomographic inspections, and ultrasonic inspections. The general operating principles of these methods as well as their main advantages, limitations and application areas are described below.</abstract>

A Brief Review on NDT&amp;E Methods For Structural Aircraft Components

<abstract xmlns="http://www.w3.org/1999/xhtml">Barely visible impact damage is one of the problems commonly occurring in composite elements during an aircraft operation. The authors described the mechanisms of impact damage formation and propagation in composite structures. The paper presents a performed analysis of an influence of impact parameters on the resulting damage, i.e. its detectability by means of visual observation as well as its extent determined based on ultrasonic tests results. The tests were conducted on the CFRP specimens with a wide range of impact damage cases obtained with combinations of variable impact energy and shapes of impactors. Additionally, an algorithm based on image processing and image analysis methods is proposed for the purpose of the effective evaluation of the ultrasonic data obtained.</abstract>

Institute of Fundamentals of Machinery Design

Evaluation of Impact Damage in Composite Structures Using Ultrasonic Testing

<abstract xmlns="http://www.w3.org/1999/xhtml">Parachute systems are in widespread use in aviation. Up to now, parachutes are the most uncertain air vehicles because of their complex and unsteady opening characteristics, changes in geometry up to 30% and vulnerability from unsteady atmospheric turbulence. Fatigue is a problem that the designers of long living parachute systems need to cope with. Authors demonstrate complexity of parachute exploitation and means to lower opening forces and extend service life without influencing safety.</abstract>

Fatigue Degradation of the Structure of Parachute Systems

<abstract xmlns="http://www.w3.org/1999/xhtml">The authors of the paper presented some of the models describing the process of micro-cracks’ development. In this study, the process of a selected model of micro-cracking was analyzed. In the model it was assumed that the damage to the material has some “thermodynamic properties” or rather universal properties inherent in most complex systems. In order to calculate the long-term fatigue strength properties of a structure, it is important to have a good understanding of the distribution parameters of the number of defects of different sizes. A model was built using the entropy principle, which is effectively used to test complex systems that are difficult to formalize. As a result of many experimental studies it was found that the development of fatigue damage is closely related to the process of plastic deformation of the material at the contact point of local defects. The results of computer calculations and simulations led to the conclusions presented in the final part of this paper.</abstract>

Accumulation of Fatigue Microdefects– Entropy Interpretation

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Fatigue of Aircraft Structures

 Print ISSN - 2081-7738Online ISSN - 2300-7591 The primary version of the journal is the online one. 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.  Why subscribe and read  Because, it gives information on recent works from the area of fatigue of aircraft structures. A lot of works are presented by domestic and worldwide researchers.  Why submit  Because, it gives you a chance for presentation your own works. Publication once a year. No publication charge.  Archiving  Sciendo archives the contents of this journal in Portico - digital long-term preservation service of scholarly books, journals and collections.  Plagiarism Policy  The editorial board is participating in a growing community of Similarity Check System's users in order to ensure that the content published is original and trustworthy. Similarity Check is a medium that allows for comprehensive manuscripts screening, aimed to eliminate plagiarism and provide a high standard and quality peer-review process. 