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    Wyświetlanie 1-4 z 4
    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:
    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:
    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:
    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
      Wyświetlanie 1-4 z 4

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