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Wyświetlanie 1-15 z 24
Tytuł:
Structural Health Monitoring Approach to the Aerospace Structures
Autorzy:
Dragan, K.
Powiązania:
https://bibliotekanauki.pl/articles/97815.pdf
Data publikacji:
2010
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Opis:
In the article only selected information regarding the SHM applications has been presented. These applications are associated with damage detection and damage growth monitoring. That approach has got crucial influence on the aircraft maintenance procedures. SHM ensures higher reliability and safety of the structures as well as repair monitoring. Right now in the AFIT, there is being conducted research work focused on the application of the SHM system for the integration with the aerospace structures for periodical and on-line monitoring.
Źródło:
Fatigue of Aircraft Structures; 2010, 2; 14-18
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Studying Efficiency of NDE Techniques Applied to Composite Materials in Aerospace Applications
Autorzy:
Dragan, K.
Swiderski, W.
Powiązania:
https://bibliotekanauki.pl/articles/1538180.pdf
Data publikacji:
2010-05
Wydawca:
Polska Akademia Nauk. Instytut Fizyki PAN
Tematy:
81.70.Cv
07.57.-c
62.20.M
07.05.Pj
62.20.mt
Opis:
This work presents the modern approach to the detection of various types of defects in composite structures used in aerospace. In such structures, including glass reinforced plastics and carbon reinforced plastics, different failure modes could occur at a manufacturing stage and during service life. Defects are connected with inadequate technology, poor workmanship, cycling fatigue loads, impact damage and environmental conditions. The main types of defects are delaminations, disbonds, foreign object inclusions and porosity. To detect such defects, several non destructive evaluation techniques can be applied, merely to mention ultrasonic, low frequency acoustics, infrared thermography and shearography. The use of multimode non destructive evaluation techniques enables characterization of defects which cannot be detected by using single non destructive evaluation methods. This paper demonstrates the necessity of using non destructive evaluation methods for the implementation of quality control and maintenance procedures while servicing aerospace composite elements.
Źródło:
Acta Physica Polonica A; 2010, 117, 5; 878-883
0587-4246
1898-794X
Pojawia się w:
Acta Physica Polonica A
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
Tytuł:
In-Service Flaw Detection and Quantification in the Composite Structures of Aircraft
Autorzy:
Dragan, K.
Synaszko, P.
Powiązania:
https://bibliotekanauki.pl/articles/97925.pdf
Data publikacji:
2009
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Opis:
Taking into consideration the increased usage of composites for aircraft structures there is a necessity for gathering information about structural integrity of such components. During the manufacturing of composites as well as during in service and maintenance procedures there is a possibility for damage occurrence. There is a large number of failure modes which can happen in such structures. These failure modes affect structural integrity and durability. In this work modern approach for detection of composites damage detection such as: delaminations, disbonds, foreign object inclusion and core damage has been presented. This detection is possible with the use of advanced P-C aided Non Destructive Testing methods. In the article nondestructive testing results for the composite vertical tail skins on MiG-29 aircraft will be delivered as well as some results of F-16 horizontal stabilizer and W-3 helicopter main rotor blades. Moreover some results of the composite honeycomb and sandwich structures will be presented based on the materials used in the construction of gliders and small aircraft. Factors affecting structural integrity and durability of the composites will be highlighted as well as necessity of the inspection with the use of modern NDT techniques. At the end some effort with Structural Health Monitoring connected with possibility of condition monitoring of composites will be presented.
Źródło:
Fatigue of Aircraft Structures; 2009, 1; 37-41
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:
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:
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:
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:
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:
Termograficzna metoda badań nieniszczących konstrukcji lotniczych
Thermographic method for nondestructive testing of aircraft structures
Autorzy:
Kornas, Ł.
Wiśniewski, T.
Dragan, K.
Powiązania:
https://bibliotekanauki.pl/articles/154530.pdf
Data publikacji:
2011
Wydawca:
Stowarzyszenie Inżynierów i Techników Mechaników Polskich
Tematy:
badania nieniszczące
termografia impulsowa
aluminium
kompozyt
statek powietrzny
non-destructive testing
pulsed thermography
aluminum
composite
aircraft
Opis:
W artykule opisano metodę badań nieniszczących konstrukcji lotniczych w podczerwieni wykorzystującą technikę termografii impulsowej (ang. pulsed thermography). Pomiary w podczerwieni zrealizowano na elementach konstrukcji lotniczych wykonanych ze stopów aluminium oraz coraz powszechniej stosowanych struktur kompozytowych zbrojonych włóknem węglowym lub szklanym. W takich strukturach powstają uszkodzenia zagrażające trwałości konstrukcji lotniczych takie jak: korozja (ubytkowa, ukryta, naprężeniowa, etc.); pęknięcia zmęczeniowe; wady i uszkodzenia w kompozytach (m.in. wtrącenia ciał obcych, rozwarstwienia, etc.). Zaprezentowano wyniki badań termograficznych oraz ich analizę z przeprowadzonej inspekcji struktur przekładkowych i laminarnych, w których zarejestrowano typowe nieciągłości strukturalne lub konstrukcyjne jakie mogą w nich występować. Zwrócono również uwagę na zalety i ograniczenia zastosowanej techniki badawczej.
The paper presents a method for nondestructive testing of aircraft structures using infrared pulsed thermography. In the pulsed ther-mography method, a disorder in the thermal equilibrium is intro-duced for a short time interval (a few thousandths of a second for metals) by providing a momentary portion of thermal energy. Infra-red measurements were taken on aircraft structural components made of aluminum alloys as well as of carbon- or glass-fiber rein-forced composites (use of which is increasingly more common). In such structures, damage modes that endanger the structure durability may occur. These are: corrosion (cavity, hidden, stress, etc.); fatigue cracks; defects and damage in composites (such as foreign body intrusions, delaminations, etc.). In the paper there are presented the results of thermographic testing. There is also described the analysis of the inspections performed on sandwich and laminar structures in which typical structural defects were recorded. The advantages and limitations of the pulsed thermography method are given.
Źródło:
Pomiary Automatyka Kontrola; 2011, R. 57, nr 10, 10; 1227-1229
0032-4140
Pojawia się w:
Pomiary Automatyka Kontrola
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:
Bonded Joint Monitoring of The Composite Aerospace Structures with The Use of Nde and Shm Approach
Autorzy:
Dragan, K.
Synaszko, P.
Sałaciński, M.
Latoszek, A.
Powiązania:
https://bibliotekanauki.pl/articles/97965.pdf
Data publikacji:
2011
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Źródło:
Fatigue of Aircraft Structures; 2011, 3; 16-21
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Monitoring of Crack Growth in a Structure Under a Composite Patch
Autorzy:
Sałaciński, M.
Synaszko, P.
Stefaniuk, M.
Dragan, K.
Powiązania:
https://bibliotekanauki.pl/articles/97971.pdf
Data publikacji:
2011
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Opis:
In civil as well as in military aviation, boron, carbon and aramid fiber reinforced composites are employed for the repair of metal structures. After such composite bonded repairs, the monitoring of the repaired structure along with the composite patch and its bond is necessary. The paper describes the possibilities of utilizing NDT methods for periodical check-ups and examinations. Also, a novel approach to continuous monitoring of the repaired structure is presented.
Źródło:
Fatigue of Aircraft Structures; 2011, 3; 103-111
2081-7738
2300-7591
Pojawia się w:
Fatigue of Aircraft Structures
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Diagnostics of Composite Aircraft Structures Using Non-Destructive Tests with Thermographic, Ultrasound and Acoustic Methods
Autorzy:
Dragan, K.
Kornas, Ł.
Latoszek, A.
Salaciński, M.
Powiązania:
https://bibliotekanauki.pl/articles/97843.pdf
Data publikacji:
2010
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Źródło:
Fatigue of Aircraft Structures; 2010, 2; 19-22
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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