Informacja

Drogi użytkowniku, aplikacja do prawidłowego działania wymaga obsługi JavaScript. Proszę włącz obsługę JavaScript w Twojej przeglądarce.

English (EN)·Polski (PL)·Yкраїнський (UK)
Przejdź do strony domowej biblioteki Centralna Biblioteka Wojskowa Link otwiera się w nowym oknie Logo biblioteki Prolib Integro - strona głównaCentralna Biblioteka Wojskowa

Wyszukujesz frazę "Synaszko, Piotr" wg kryterium: Autor

  Lista filtrów
Wyrównaj
    Wyświetlanie 1-8 z 8
    Tytuł:
    Application of Digital Radiography (Dr) in an Approach to Evaluate the Technical Condition of MiG-29’s Vertical Stabilizers
    Autorzy:
    Luziński, Rafał
    Synaszko, Piotr
    Dragan, Krzysztof
    Powiązania:
    https://bibliotekanauki.pl/articles/2105179.pdf
    Data publikacji:
    2021
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    NDT
    digital radiography
    inspection of internal structures
    composite structures
    Opis:
    The purpose of the work presented was to evaluate the capabilities of digital radiography to detect cracks in the internal structure of MiG-29 vertical stabilizers. The test object was a stabilizer previously subjected to fatigue testing and partially torn down for the needs of visual inspection. An inspection of three regions containing cracked parts was performed, with use of a pulsed x-ray generator and digital detector array. The results confirmed the method could be used to detect cracks in an internal structure which could not be inspected with other methods without affecting the stabilizer’s integrity.
    Źródło:
    Fatigue of Aircraft Structures; 2021, 13; 1--7
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Analysis of the Corrosion Resistance of Aircraft Structure Joints with Double-Sided Rivets and Single-Sided Rivets
    Autorzy:
    Kamińska, Paulina
    Synaszko, Piotr
    Ciężak, Patryk
    Dragan, Krzysztof
    Powiązania:
    https://bibliotekanauki.pl/articles/2105143.pdf
    Data publikacji:
    2020
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    rivet joints
    double-sided rivets
    one-sided rivets
    corrosion
    accelerated ageing tests
    Opis:
    An important factor having a negative impact on the technical condition of aircraft structure elements is the adverse effect of the atmosphere, which causes formation of corrosion in aircraft structures, especially in riveted lap joints. The electric potential difference between the sheet material and the rivet, in the presence of humid air, may cause electrochemical corrosion. The paper presents specimens that imitate the repair on the Mi-24 helicopter with the use of blind rivets in places where solid double-sided rivets could not be used.The aim of the research was to assess the corrosion resistance of lap joints with the use of single-sided and double-sided rivets. The analysis of corrosion resistance was carried out based on accelerated aging tests in a salt spray chamber. The salt chamber tests were aimed at determining the changes taking place in the specimens exposed to the marine environment. In the course of periodic observations changes in the mass of the specimens and in the form of corrosion losses were recorded. These activities were aimed at determining whether the exposure of specimens in the salt chamber causes electrochemical corrosion or pillowing. In addition, the specimens were subjected to static strength tests to assess the effect of corrosion on the strength properties of riveted joints.
    Źródło:
    Fatigue of Aircraft Structures; 2020, 12; 57--68
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Comparison of Pulse Thermography (PT) and Step Heating (SH) Thermography in Non-Destructive Testing of Unidirectional GFRP Composites
    Autorzy:
    Kamińska, Paulina
    Ziemkiewicz, Jarosław
    Synaszko, Piotr
    Dragan, Krzysztof
    Powiązania:
    https://bibliotekanauki.pl/articles/97879.pdf
    Data publikacji:
    2019
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    pulsed thermography
    step-heating thermography
    composites
    NDT
    NDE
    GFRP
    Opis:
    This paper presents two techniques of active thermography i.e. the pulsed thermography technique and the step heating technique. The aim of this article is to compare these two techniques and present the possibilities, advantages and limitations of their use in the context of non-destructive testing of composite materials. The experimental section presents the results of tests carried out on samples of the polymer composites reinforced with glass fiber.
    Źródło:
    Fatigue of Aircraft Structures; 2019, 11; 87-102
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Comparative Study on Fatigue Life of CFRP Composites with Damages
    Autorzy:
    Baran, Marta
    Synaszko, Piotr
    Lisiecki, Janusz
    Kłysz, Sylwester
    Powiązania:
    https://bibliotekanauki.pl/articles/97921.pdf
    Data publikacji:
    2019
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    CAI
    CFRP
    compression
    Compression After Impact
    damage
    drop-weight impact test
    fatigue test
    residual strength
    Opis:
    In this work, the compressive residual strength tests results, Compression After Impact (CAI), are presented. The specimens were made of carbon-epoxy prepreg E722-02 UHS 130-14. Two variants of specimens were tested: samples undamaged and samples with damage that was centrally introduced by a drop-weight impact, as per the ASTM D7136/7136M standard. An impactor with potential energy equal to 15J and the type of support required by the standard were used. The size of impacted damages, defined as an area of damage on a plane perpendicular to the impact direction, and the equivalent diameter were specified using the flash thermography method. The tests were performed using the fixtures manufactured according to the ASTM D7137/7137M standard. The specimens were compressed to determine the residual strength. This value was afterwards used to specify the force levels for the fatigue tests. The fatigue tests were carried out under force control – with a sinusoidal shape, stress ratio R equal to 0.1 and frequency f 1Hz. Maximum force in a loading cycle Pmax was being increased after each thousand of cycles N until its value was close to the residual strength determined in the previously mentioned tests. In this work, the following relationships were presented: force-displacement P-δ for both static and fatigue tests and displacement-loading cycles δ-N for fatigue tests. A method of conducting the fatigue tests of CFRP composite was proposed, in which both the CAI specimens and CAI fixture were used. This allowed researchers to accelerate making initial comparisons between the two groups of specimens with damages – grouped relative to the way of conditioning.
    Źródło:
    Fatigue of Aircraft Structures; 2019, 11; 28-38
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    A Comparison of Composite Specimens Damage area Measurements Performed using Pulsed Thermography and Ultrasonic NDT Methods
    Autorzy:
    Luziński, Rafał
    Ziemkiewicz, Jarosław
    Synaszko, Piotr
    Żyluk, Andrzej
    Dragan, Krzysztof
    Powiązania:
    https://bibliotekanauki.pl/articles/97835.pdf
    Data publikacji:
    2019
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    NDT
    NDI
    ultrasonics
    infrared thermography
    CFRP
    BVID
    impact damage
    composite structures
    Opis:
    Carbon fiber reinforced plastics (CFRPs) are widely used in aerospace structures due to their high stiffness, strength and good fatigue properties. They are however vulnerable to loads perpendicular to their plane and, while impacted, can suffer significant internal damage decreasing their overall strength. Detecting and sizing such damage is an important task of the non-destructive inspection (NDI) methods. This study was conducted to detect and quantify damage in a set of six impacted even rectangular CFRP specimens designed from a MiG-29 vertical stabilizer’s skin. The inspection was done using the ultrasonic (UT) method (based on mobile scanner – MAUS V) and the pulsed infrared thermographic (IRT) method. Each specimen’s inside and outside (impacted) surface was inspected separately with IRT, while the outside surface was then inspected with UT. UT provided the most precise measurements of the damage area, while the IRT inspection of the outside surface (which would be accessible on a real aircraft structure) provided underestimated values due to the damage’s depth and geometry.
    Źródło:
    Fatigue of Aircraft Structures; 2019, 11; 68-77
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Examination of Honeycomb Core Compliance in Sandwich Structure
    Autorzy:
    Nowakowski, Dominik
    Baran, Marta
    Lisiecki, Janusz
    Kłysz, Sylwester
    Synaszko, Piotr
    Powiązania:
    https://bibliotekanauki.pl/articles/97919.pdf
    Data publikacji:
    2019
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    honeycomb core
    horizontal stabilizer
    MiG-29 fighter jet
    static compression test
    compliance
    Opis:
    The objective of the research presented in this paper was to determine the honeycomb core compliance of a sandwich structure of the horizontal stabilizer of the MiG-29 fighter jet in the static compression test. The study of the specimen was conducted based on the ASTM C365/C365M standard. The article presents the results of experimentally determined dependencies and strength parameters, i.e. the force-displacement dependence, the compressive modulus and the honeycomb core deformations.
    Źródło:
    Fatigue of Aircraft Structures; 2019, 11; 19-27
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Use of a composite repair patches to repair the upper air intake flap for the MiG-29 aircraft engine = Zastosowanie kompozytowego pakietu naprawczego do naprawy klapki górnego wlotu powietrza do silnika samolotu MIG-29
    Zastosowanie kompozytowego pakietu naprawczego do naprawy klapki górnego wlotu powietrza do silnika samolotu MIG-29
    Autorzy:
    Lisiecki, Janusz.
    Powiązania:
    Aviation Advances & Maintenance / Air Force Institute of Technolog 2017, nr 2, s. 101-114, 115-127
    Współwytwórcy:
    Sałaciński, Michał. Autor
    Stefaniuk, Michał. Autor
    Synaszko, Piotr. Autor
    Data publikacji:
    2017
    Tematy:
    Samoloty myśliwskie
    Mikojan MiG-29 (samolot)
    Silniki
    Budowa i konstrukcje
    Remont
    Kompozyty
    Analiza numeryczna
    Badania naukowe
    Artykuł z czasopisma naukowego
    Opis:
    Bibliografia na stronach 114, 127.
    Dostawca treści:
    Bibliografia CBW
    Artykuł
      Wyświetlanie 1-8 z 8

      Ta witryna wykorzystuje pliki cookies do przechowywania informacji na Twoim komputerze. Pliki cookies stosujemy w celu świadczenia usług na najwyższym poziomie, w tym w sposób dostosowany do indywidualnych potrzeb. Korzystanie z witryny bez zmiany ustawień dotyczących cookies oznacza, że będą one zamieszczane w Twoim komputerze. W każdym momencie możesz dokonać zmiany ustawień dotyczących cookies