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Wyszukujesz frazę "Sałaciński, M." wg kryterium: Autor

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    Wyświetlanie 1-7 z 7
    Tytuł:
    Diagnosis and Repair Technology of Damaged Elements of Casa Aircraft
    Autorzy:
    Salacinski, M.
    Synaszko, P.
    Olszak, R.
    Powiązania:
    https://bibliotekanauki.pl/articles/97837.pdf
    Data publikacji:
    2010
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Opis:
    Recently Polish Air Force has been equipped with new types of aircraft. New aircraft have many elements made of composites. Composites enable increasing performance but also pose new challenges. One of these challenges is the necessity of repairing after damage. This paper presents the results of the non-destructive inspection (MIA, conductivity, optical measurement ) of the C-295 plane after damage. Some parts made of composites and metal were damaged. In this paper, the authors propose a technology of repairing damaged parts.
    Źródło:
    Fatigue of Aircraft Structures; 2010, 2; 98-105
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Using Sandblasting and Sol Gel Techniques for the Preparation of a Metal Surface and Their Effects on the Durability of Epoxy-Bonded Joints
    Autorzy:
    Sałaciński, M.
    Zabłocka, M.
    Synaszko, P.
    Powiązania:
    https://bibliotekanauki.pl/articles/97751.pdf
    Data publikacji:
    2012
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    epoxy-bonded joints
    composite structures
    repair
    sandblasting treatment
    aerospace
    Opis:
    The epoxy-bonded joints are widely employed in aerospace in the Composite Patch Bonded Repair (CPBR) method used for repair metallic and composite structures. The properties of epoxy usually meet the mechanical and environmental requirements, but the durability of bonded joints depends also on the surface preparation. The most common techniques used for the surface preparation are Forest Product Laboratory’s (FPL) technique and Phosphoric Acid Anodizing (PAA). Both methods ensure very good adhesion but they have some disadvantages. They require the application of toxic and aggressive acids, dangerous for the operator. Also, the use of acids for cleaning the surfaces can cause corrosion. The sandblasting treatment of metal surfaces ensures quite good adhesion. This technique requires neither specialist equipment nor the use of toxic substances. Recommended by the Royal Australian Air Force (RAAF) the technique is also used by the Air Force Institute of Technology. Sol Gel is a new product developed for the treatment of metal surfaces before bonding. It is not hazardous for the operator and it does not cause corrosion due to its specific chemical composition. The article describes the behavior of bonded joints between two metal surfaces prepared using sandblasting and Sol Gel. The investigations were carried out in various environment conditions according to the ASTM Standards.
    Źródło:
    Fatigue of Aircraft Structures; 2012, 4; 94-99
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    The Effect of Environmental Flight Conditions on Damage Propagation in Composite Sandwich Structure
    Autorzy:
    Synaszko, P.
    Sałaciński, M.
    Kornas, Ł.
    Powiązania:
    https://bibliotekanauki.pl/articles/97791.pdf
    Data publikacji:
    2015
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    honeycomb structures
    detection of water ingress
    thermografic techniques
    Opis:
    The aim of the study was to determine the traceability of damage growth caused by inclusions of water in the composite sandwich structure. It was assumed that as a result of temperature changes during the flight and accompanying phase transformation, the zone containing water inclusions increases. The growth is caused by the destruction (mainly the tearing of walls) of the core. As part of the work, this assumption was verified experimentally. For the experiment to be successful it was necessary to simulate actual flight conditions. The simulation involved inducing phase transformations of water in the core cell as a function of time and temperature. Before and after the experiments the non-destructive tests using pulsed thermography were performed. The test results revealed an increase in the number of cells occupied by water. Adequate specimens were designed and manufactured. The study showed that cyclical changes in temperature affected the propagation of water in core sandwich structures. Further, it was found that the increase in the surface area of water-containing inclusions could be monitored using thermographic techniques.
    Źródło:
    Fatigue of Aircraft Structures; 2015, 7; 24-27
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    The Effect of Cure Cycle Time on the Properties of Epoxy-Bonded Joints
    Autorzy:
    Zabłocka, M.
    Sałaciński, M.
    Synaszko, P.
    Kłysz, S.
    Powiązania:
    https://bibliotekanauki.pl/articles/97969.pdf
    Data publikacji:
    2012
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    epoxy-bonded joints
    cure cycle
    Composite Patch Bonded Repair (CPBR)
    Opis:
    This paper presents the results of the study of the properties of epoxy-bonded joints. Depending on the parameters of cure cycles the epoxy adhesive film has got various mechanical properties. When it is possible to use cure parameters suggested in the data sheet of the adhesive film the best results are obtained. However, in aerospace applications the cure cycle depends on the thermal resistance of other aircraft elements including electrical equipment, cables, etc., and is different from the recommended in the data sheet. Composite Patch Bonded Repair (CPBR) is a special methodology, where the patch cure cycle and the bonding process must be carried out in one operation. The adhesive film cure cycle parameters depend on the prepreg cure cycle parameters. The purpose of this research is to define the influence of a prolonged cure cycle of the adhesive film on the bonded layer strength properties. The metal surface of the specimen has been prepared for bonding by sandblasting and the use of Corrosion Inhibiting Primer BR 127. The tests were performed with the use of Structural Adhesive Film AF 163-2 and two types of cure cycles: the cycle recommended by the data sheet - 121ºC/60 min and the prolonged one - 121ºC/105 min. After the cure cycle the thickness of the bonded layer was measured. Both specimens were comparatively tested during the following strength tests of the bonded layer: static breaking tests using the wedge and the shear strength investigations. The surface of the bonded layer was observed during the tests by an electronic microscope (100x, 200x), which made it possible to demonstrate the effect of the cure cycle on the porosity and observe the nature of the bonded layer damage – de-cohesive and de-adhesive.
    Źródło:
    Fatigue of Aircraft Structures; 2012, 4; 157-161
    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:
    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:
    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
      Wyświetlanie 1-7 z 7

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