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Wyświetlanie 1-15 z 24
Tytuł:
Evaluation of Impact Damage in Composite Structures Using Ultrasonic Testing
Autorzy:
Wronkowicz-Katunin, A.
Dragan, K.
Powiązania:
https://bibliotekanauki.pl/articles/97897.pdf
Data publikacji:
2018
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
impact damage
composite structures
non-destructive testing
ultrasonic testing
image analysis
Opis:
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.
Źródło:
Fatigue of Aircraft Structures; 2018, 10; 82-92
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Enhancement of Damage Detectability in Aircraft Structures Using the Fusion of NDT Results
Autorzy:
Zapłotny, M.
Katunin, A.
Dragan, K.
Powiązania:
https://bibliotekanauki.pl/articles/97990.pdf
Data publikacji:
2017
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
aircraft composite structures
ultrasonic testing
information fusion
non-destructive testing
Opis:
Following the damage tolerance philosophy in aircraft design and operation, one of the most significant stages of maintenance is non-destructive testing of structures. It is, therefore, essential to use testing methods sensitive to particular damage types occurring in aircraft structures during operation. In this paper, the authors present a study on selection and comparison of methods of information fusion applied to testing the results of inspection of composite structures used in aircraft elements, obtained using various ultrasonic methods. The presented approach of fusion of ultrasonic scans allows for enhancement of damage detection and identification due to the presence of different parts of information about detected damage obtained from different initial information sources in a single resulting set. Such an approach can be helpful at the decision-making stage during inspection of aircraft elements and structures. Besides the methodology, the GUI-based software for performing fusion of various types of ultrasonic data is presented.
Źródło:
Fatigue of Aircraft Structures; 2017, 9; 55-74
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Fatigue Cracks Detection using PZT Transducers under the Influence of Uncertain Environmental Factors
Autorzy:
Dziendzikowski, M.
Klimaszewski, S.
Dragan, K.
Powiązania:
https://bibliotekanauki.pl/articles/97945.pdf
Data publikacji:
2016
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
structural health monitoring
PZT transducers
fatigue cracks detection
environmental factors compensation
Opis:
This paper presents technique for qualitative assessment of fatigue crack growth monitoring, utilizing guided elastic waves generated by the sparse PZT piezoelectric transducers network in the pitch – catch configuration. Two Damage Indices (DIs) correlated with the total energy received by a given sensor are used to detect fatigue cracks and monitor their growth. The indices proposed carry marginal signal information content in order to decrease their sensitivity with respect to other undesired non-controllable factors which may distort the received signal. The reason for that is to limit the false calls ratio which besides the damage detection capability of a system, plays a crucial role in applications. However, even such simplified damage indices can alter over a long term, leading to the misclassification problem. Considering a single sensing path, it is very difficult to distinguish whether the resultant change of DIs is caused by a damage or due to decoherence of these DIs. Therefore, assessment approaches based on threshold levels fixed separately for DIs obtained on each of the sensing paths, would eventually lead to a false call. An alternative approach is to compare changes of DIs for all sensing paths. Developing damage distorts the signal only for the sensing paths in its proximity. In order to decrease the misclassification risk, a method of compensating such DIs drift is proposed. The main features and damage detection capabilities of this method will be demonstrated by conducting a laboratory fatigue test of an aircraft panel. The proposed approach has been verified on a real structure during fatigue test of a helicopter tail boom.
Źródło:
Fatigue of Aircraft Structures; 2016, 8; 111-115
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Review of Aeronautical Fatigue Investigations in Poland (2013-2014)
Autorzy:
Niepokólczycki, A.
Leski, A.
Dragan, K.
Powiązania:
https://bibliotekanauki.pl/articles/97803.pdf
Data publikacji:
2016
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
fatigue of aircraft structures
Opis:
This review was presented on the 34 Conference of the International Committee on Aeronautical Fatigue and Structural Integrity, Helsinki, Finland, June 1-2, 2015. It contains description of main works and investigations in fatigue of aircraft structures performed in Poland during the years 2013 and 2014.
Źródło:
Fatigue of Aircraft Structures; 2016, 8; 5-48
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Composite Aerospace Structure Monitoring with use of Integrated Sensors
Autorzy:
Dragan, K.
Dziendzikowski, M.
Kurnyta, A.
Salacinski, M.
Klysz, S.
Leski, A.
Powiązania:
https://bibliotekanauki.pl/articles/97867.pdf
Data publikacji:
2015
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
structural health monitoring
PZT sensor network
barely visible impact damages
Opis:
One major challenge confronting the aerospace industry today is to develop a reliable and universal Structural Health Monitoring (SHM) system allowing for direct aircraft inspections and maintenance costs reduction. SHM based on guided Lamb waves is an approach capable of addressing this issue and satisfying all the associated requirements. This paper presents an approach to monitoring damage growth in composite aerospace structures and early damage detection. The main component of the system is a piezoelectric transducers (PZT) network integrated with composites. This work describes sensors’ integration with the structure. In particular, some issues concerning the mathematical algorithms giving information about damage from the impact damage presence and its growth are discussed.
Źródło:
Fatigue of Aircraft Structures; 2015, 7; 12-17
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Predictive Models for Transient Loads of the Vertical Stabilizer of an Aircraft developed using Canonican Correlation Analision
Autorzy:
Dziendzikowski, M.
Zieliński, W.
Obrycki, Ł.
Woch, M.
Synaszko, P.
Dragan, K.
Leski, A.
Powiązania:
https://bibliotekanauki.pl/articles/97795.pdf
Data publikacji:
2015
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
damage tolerance
loads prediction
loads monitoring
Opis:
Knowledge about loads occurring in the structure during aircraft operation is vital from the point of view of the damage tolerance approach to aircraft design. In the best-life scenario, such information could be available from a network of sensors, e.g. strain gauges, installed in the aircraft structure to measure local stresses. However, operational loads monitoring (OLM) systems are still not widely applied. Instead, what is available is a set of flight parameters, which by the laws of inertia and aerodynamics help determine the dominant part of loads acting on a given element. This paper discusses the canonical correlation analysis (CCA) as a method for selecting the flight parameters used to predict aircraft loads. CCA allows for the identification of both different modes of stress distribution as well as flight parameters which are best suited for their prediction. The paper presents the application of this method to identify loads acting on the vertical stabilizer of an aircraft.
Źródło:
Fatigue of Aircraft Structures; 2015, 7; 41-46
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
An Approach to Structural Health Monitoring of Composite Structures Based on Embedded PZT Transducers
Autorzy:
Dziendzikowski, M.
Dragan, K.
Kurnyta, A.
Kornas, Ł.
Latoszek, A.
Zabłocka, M.
Kłysz, S.
Leski, A.
Chalimoniuk, M.
Giewoń, J.
Powiązania:
https://bibliotekanauki.pl/articles/97829.pdf
Data publikacji:
2014
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
structural health monitoring
PZT sensor network
barely visible impact damages
Opis:
One approach to developing a system of continues automated monitoring of structural health is to use elastic waves excited in a given medium by a piezoelectric transducers network. Depending on their source and the geometry of the structure under consideration elastic waves can propagate over a significant distance. They are also sensitive to local structure discontinuities and deformations providing a tool for detecting local damage in large aerospace structures. This paper investigates the issue of Barely Visible Impact Damages (BVIDs) detection in composite materials. The model description and the results of impact tests verifying damage detection capabilities of the proposed signal characteristics are presented in the paper.
Źródło:
Fatigue of Aircraft Structures; 2014, 6; 113-118
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
An On-Line Multiway Approach to In-Situ NDI Looking at the PZL-130TCII
Autorzy:
Dragan, K.
Dziendzikowski, M.
Kurnyta, A.
Latoszek, A.
Leski, A.
Kłysz, A.
Powiązania:
https://bibliotekanauki.pl/articles/97811.pdf
Data publikacji:
2013
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
structural health monitoring
PZT sensor network
fatigue crack detection
full scale fatigue test
Opis:
Providing a reliable and universal Structural Health Monitoring (SHM) system allowing for remote aircraft inspections and a reduction of maintenance costs is a major challenge confronting the aerospace industry today. SHM based on guided Lamb waves is one of the approaches capable of addressing the issue while satisfying all the associated requirements. This paper presents a holistic approach to the continuous real time damage growth monitoring and early damage detection in aircraft structure. The main component of the system is a piezoelectric transducers (PZT) network. It is complemented by other SHM methods: Comparative Vacuum Monitoring (CVMTM) and Resistance Gauges at selected aircraft hot spots. The paper offers the description of damage detection capabilities including the analysis of data collected from the PZL-130 Orlik aircraft full-scale fatigue test.
Źródło:
Fatigue of Aircraft Structures; 2013, 5; 5-11
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Assessment of Sensor Technologies for Aircraft SHM Systems
Autorzy:
Kurnyta, A.
Dragan, K.
Dziendzikowski, M.
Powiązania:
https://bibliotekanauki.pl/articles/97915.pdf
Data publikacji:
2013
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
SHM
sensor
fatigue crack
crack detection methods
usage monitoring
Opis:
SHM is a monitoring system which uses sensors, actuators and data transmission, acquisition and analysis, permanently integrated with the inspected object. The objective of SHM is to detect, localize, identify and predict development of fatigue fractures, increasing safety and reliability. This paper presents an assessment of sensor technologies used in aircraft SHM system. Due to the fact that most of these measurement methods are relatively new and still under development the present appraisal focuses on a number of parameters with reference to each method, including a sensor’s installation issues, reliability, power consumption, sensor infrastructure, sensitivity and cost and availability. The work is predominantly focused on the assessment of permanently bonded sensors, such as foil strain gages, Comparative Vacuum Monitoring (CVM), Piezo sensors (PZT), Eddy-Current Transducers (ECT). Finally, all these methods are briefly discussed.
Źródło:
Fatigue of Aircraft Structures; 2013, 5; 53-59
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Reconstruction of delivery positions in the city of Celje, Slovenia
Wiederaufbau von dem lieferposition in stadt Celje, Slowenien
Autorzy:
Dragan, D.
Vizinger, T.
Intihar, M.
Kramberger, B.
Fosner, M.
Prah, K.
Powiązania:
https://bibliotekanauki.pl/articles/374228.pdf
Data publikacji:
2013
Wydawca:
Politechnika Śląska. Wydawnictwo Politechniki Śląskiej
Tematy:
location problems
maximal covering problems
optimization
simulation
GIS
urban freight transport
problemy lokalizacji
optymalizacja
symulacja
miejski transport towarowy
Opis:
The paper addresses the problem of the reconstruction and allocation of delivery positions in the urban area. The aim is to achieve the optimal reorganization of urban freight transport in old town core in the municipality of Celje. Optimal allocation relies on optimization based on the Monte Carlo simulation and represents a first stage of a two-stage optimization approach to re-design the existing urban freight transport. The number of optimal delivery positions is required to be as minimal as possible, which can still assure a maximal service area within the prescribed radius, while keeping the minimal walking distances of delivery personnel between the nearest delivery position and the customer’s physical location. The main issues of the used heuristic allocation algorithm and the presentation of calculated results are provided. In the near future, the calculated delivery positions are going to be used for the purpose of physical implementation in order to improve the existing delivery transport.
Der Artikel behandelt das Problem der Wiederaufbau und Allokation von den Lieferung Positionen in einem städtischen Gebiet. Der Zweck ist die optimale Reorganisation des städtischen Güterverkehrs im alten Stadtkern in der Gemeinde Celje zu Erreichen. Die optimale Allokation basiert auf der Optimierung auf Basis der Monte-Carlo-Simulationen und stellt die erste Stufe einer zweistufigen Optimierung Verfahren zur Re-Designs der bestehenden städtischen Güterverkehrs. Die Anzahl der optimalen Lieferpositionen sollte so wenig wie möglich sein, aber trotzdem einen maximalen Service-Bereich innerhalb des vorgeschriebenen Radius gewährleisten. Gleichzeitig sollte die Entfernung zwischen den nächstgelegenen Lieferpositionen und Kunden Positionen kleinstmöglich sein. Die wichtigsten Themen des verwendeten Heuristic Zuordnungsalgorithmus und die Darstellung der berechneten Ergebnisse sind gegeben. Die Standorte der berechneten Lieferung Positionen werden zum Zwecke der physikalischen Implementierung genutzt, um den bestehenden Güterverkehr zu verbessern
Źródło:
Transport Problems; 2013, 8, 2; 11-23
1896-0596
2300-861X
Pojawia się w:
Transport Problems
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
An Approach to Damage Detection in the Aircraft Structure with the Use of Integrated Sensors – The Symost Project
Autorzy:
Dragan, K.
Dziendzikowski, M.
Leski, A.
Dworakowski, Z.
Uhl, T.
Powiązania:
https://bibliotekanauki.pl/articles/97801.pdf
Data publikacji:
2012
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
averaged damage index
full scale fatigue test
damage growth monitoring
Opis:
This paper presents an approach to damage growth monitoring and early damage detection in the structure of PZL – 130 ORLIK TC II turbo-prop military trainer aft using the statistical models elaborated by the Polish Air Force Institute of Technology (AFIT) and the network of the sensors attached to the structure. Drawing on the previous experiences of the AFIT and AGH in structural health monitoring, the present research will deploy an array of the PZT sensors in the structure of the PZL -130 Orlik TC II aircraft. The aircraft has just started Full Scale Fatigue Test (FSFT) that will continue up to 2013. The FSFT of the structure is necessary as a consequence of the structure modification and the change of the maintenance system - the transition to Condition Based Maintenance. In this paper, a novel approach to the monitoring of the aircraft hot-spots will be presented. Special attention will be paid to the preliminary results of the statistical models that provide an automated tool to infer about the presence of damage and its size. In particular, the effectiveness of the selected signal characteristics will be assessed using dimensional reduction methods (PCA) and the so-called averaged damage indices will be delivered. Moreover, the results of the signal classification based on the neural network will be presented alongside the numerical model of the wave propagation. The work contains selected information about the project scope and the results achieved at the preliminary stage of the project.
Źródło:
Fatigue of Aircraft Structures; 2012, 4; 10-16
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Damage Detection and Size Quantification of FML with the Use of NDE
Autorzy:
Dragan, K.
Kornas, Ł.
Kosmatka, M.
Leski, A.
Sałaciński, M.
Synaszko, P.
Bieniaś, J.
Powiązania:
https://bibliotekanauki.pl/articles/98012.pdf
Data publikacji:
2012
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
fibre metal laminates
composites
non-destructive testing
Opis:
Composite materials have been developed in recent years. A new generation of structural composite materials for advanced aircraft is Fibre Metal Laminates (FML). They are hybrid composites consisting of alternating thin layers of metal sheets and fiber-reinforced composite material. FMLs have both low weight and good mechanical properties (high damage tolerance: fatigue and impact characteristics, corrosion and fire resistance). Quality control of materials and structures in aircraft is an important issue, also for Fibre Metal 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 relevant defects that should be detected by non-destructive testing are porosity and delaminations. In this paper, a number of different non-destructive methods for the inspection of Fibre Metal Laminates were studied. The possibility of quality control of manufactured FML laminates - detection of defects as well as the procedures and processes are presented and discussed.
Źródło:
Fatigue of Aircraft Structures; 2012, 4; 5-9
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Recent Progress in Full Scale Fatigue Test of PZL-130 "Orlik" TC-II Structure
Autorzy:
Reymer, P.
Leski, A.
Dragan, K.
Powiązania:
https://bibliotekanauki.pl/articles/97765.pdf
Data publikacji:
2012
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
full scale fatigue test
non-destructive inspection
teardown inspection
quantitative fractography
Opis:
This article presents preparation of the Full Scale Fatigue Test of the PZL-130 "Orlik" TC-II. After completing the flight load acquisition stage [1] a load block representing 200 Simulated Flight Hours in 194 flights was developed. This load block was further modified in order to introduce fatigue markers on the crack surface [2] visible during Quantitative Fractography, planned to take place during the Teardown Inspection of the structure after completion of the test. Meanwhile, the test rig along with the loading system and the test specimen were prepared at Výzkumný a Zkušební Letecký Ústav (VZLU, Prague, Czech Republic). The test specimen, consisting of the overhauled fuselage, modernized wings and the landing gear, was instrumented with the identical strain gauge measuring system as presented in [3], which was calibrated before the commencement of fatigue testing. Finally, some preliminary issues encountered during the fatigue test startup were highlighted and the outline for future work was described.
Źródło:
Fatigue of Aircraft Structures; 2012, 4; 76-81
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Uniwersalne wskaźniki uszkodzeń w systemach monitorowania struktury statków powietrznych
Universal damage indices in aircraft Structural Health Monitoring systems
Autorzy:
Dragan, K.
Dziendzikowski, M.
Powiązania:
https://bibliotekanauki.pl/articles/208526.pdf
Data publikacji:
2012
Wydawca:
Wojskowa Akademia Techniczna im. Jarosława Dąbrowskiego
Tematy:
systemy monitorowania uszkodzeń
wskaźniki uszkodzeń
stan struktury
diagnostyka
structural health monitoring
damage indices
structure health
damage detection
Opis:
Systemy monitorowania struktury (SHM) stanowią jedną z najintensywniej rozwijanych technologii, mających na celu zwiększenie bezpieczeństwa eksploatacji statków powietrznych. Wnioskowania o stanie diagnozowanej struktury dokonuje się zazwyczaj na podstawie tzw. wskaźników uszkodzeń otrzymanych z różnorodnych charakterystyk sygnału rejestrowanego przez sensory układu monitorującego. W niniejszej pracy zbadana zostanie efektywność wybranych wskaźników uszkodzeń w ocenie stanu konstrukcji używanych w lotnictwie przy pomocy systemu monitorowania wykorzystującego generację fal sprężystych. Zaproponowane zostaną również wskaźniki uszkodzeń o charakterze uniwersalnym, pozwalające wnioskować o stanie struktury w dużym stopniu niezależnie od jej typu i lokalizacji występujących uszkodzeń.
Structural health monitoring (SHM) is an aircraft operation safety enhancing technology which nowadays undergoes rapid development. Structural health of a test structure is inferred from damage indices - various characteristics of the signal registered by transducers of the monitoring system. In this paper, we investigate the efficiency of selected damage indices in the evaluation of the health of structures used in aviation. We propose also damage indices having universal properties, useful in structural health assessment irrespectively of its type and the damage localization.
Źródło:
Biuletyn Wojskowej Akademii Technicznej; 2012, 61, 2; 405-417
1234-5865
Pojawia się w:
Biuletyn Wojskowej Akademii Technicznej
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Analysis of the Possibility to Assess the Occurrence of Hidden Corrosion in Lap Joints Using Active Thermography
Autorzy:
Kornas, Ł.
Dragan, K.
Powiązania:
https://bibliotekanauki.pl/articles/97877.pdf
Data publikacji:
2011
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Opis:
The article details the NDT technique of pulse thermography used for objective diagnosis of riveted lap joints construction. The degradation of materials manifesting in corrosion is inherent in the process of aircraft operation. One type of corrosion is galvanic corrosion occurring in the overlap joints (known as hidden corrosion). As a result of the potential difference between the two layers of the aluminum alloy skin, there occurs the phenomenon of oxidation of the material, producing corrosion products in the form of oxide compounds characterized by heat properties different than those of the base material. Active thermography techniques allow observing infrared energy, which changes due to the difference of thermal properties of the tested materials.
Źródło:
Fatigue of Aircraft Structures; 2011, 3; 53-56
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Wyświetlanie 1-15 z 24

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