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    Wyświetlanie 1-9 z 9
    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:
    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:
    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:
    Introduction of an Individual Aircraft Tracking Program for the Polish Su-22
    Autorzy:
    Reymer, P.
    Kurdelski, M.
    Leski, A.
    Leśniczak, A.
    Dziendzikowski, M.
    Powiązania:
    https://bibliotekanauki.pl/articles/97847.pdf
    Data publikacji:
    2017
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    Individual Aircraft Tracking
    Su-22 fighter-bomber
    Opis:
    The Su-22 fighter-bomber is a military aircraft used in the Polish Air Force (PLAF) since the mid 1980’s. By decision of the Ministry of National Defence Republic of Poland, the assumed service life for this type of aircraft was prolonged up to 3200 flight hours based on the Full Scale Fatigue Test (FSFT) results. The FSFT was conducted using the real load profile defined during the Operational Load Monitoring Program (OLM) and the 3200 hour service life was also based on this load profile. In order to assure safe operation of all the 18 Su-22 aircraft, the Individual Aircraft Tracking program was introduced. The program was based on the results of the FSFT as well as the analysis of the flight parameters recorded by the THETYS onboard flight recorder. In this paper, the authors present the methodology, assumed fatigue hypothesis and preliminary results of the IAT program for the Polish Su-22.
    Źródło:
    Fatigue of Aircraft Structures; 2017, 9; 101-108
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    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:
    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 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:
    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
      Wyświetlanie 1-9 z 9

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