Temat: laminates - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: The Influence of Material Configuration of Fibre-Metal Laminates with Alumina Core on Flexural Strength
Autorzy:: Frankiewicz, Mariusz
Karoluk, Michał
Dziedzic, Robert
Timmel, Tristan
Scholz, Peter
Powiązania:: https://bibliotekanauki.pl/articles/24201172.pdf
Data publikacji:: 2022
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: fibre-metal laminates
flexural strength
fatigue
composite materials
Opis:: Fibre metal laminates (FMLs) consisting of layers made of PA6 polyamide prepregs reinforced with glass and carbon fibres and an aluminium alloy core are the new variant of the other types used by aerospace FML materials such as GLARE or CARALL. By using a thermoplastic matrix, they can be shaped by stamping processes, which allows for a more efficient production process than classical laminating methods such as vacuum bagging. In addition to the improved impact energy absorption efficiency, the metallic core can be utilised to effectively bond the composite part to adjacent metallic structures. This article presents the influence of the material configuration of fibre-metal laminates consisting of continuous fibre-reinforced thermoplastic outer layers integrated with a layer of metallic aluminium alloy inserts - a number of layers, type and direction of reinforcing fibres - on the static and fatigue flexural properties. In this study, eight laminate configurations were prepared using a one-step variothermal consolidation process. The results showed that in the three-point flexural fatigue test, the samples exceeded 106 cycles at stresses <30% of the static bending strength. Laminates with predominantly longitudinally reinforced layers showed the highest fatigue strength among the FML samples analysed. The type of reinforcing fibres and the number of layers were less affected on the analysed mechanical properties.
Źródło:: Fatigue of Aircraft Structures; 2022, 14; 18--28
2081-7738
2300-7591
Pojawia się w:: Fatigue of Aircraft Structures
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Modern process of composite structures manufacturing based on cad definition of the composite
Nowoczesny proces produkcji struktur kompozytowych w oparciu o komputerową definicję kompozytu
Autorzy:: Krauze, W.
Powiązania:: https://bibliotekanauki.pl/articles/212886.pdf
Data publikacji:: 2016
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: producibility
flat pattern
layup
laminates
CATIA CPD
kompozyty
technologiczność kompozytów
rozkroje warstw
laminaty
Opis:: The article describes benefits for composite structures manufactured with the computer aid. The evolution of manufacturing process is presented, highlighting the specifics of anisotropic and laminar properties of composites. The paper shows steps of the process, including: design, preliminary computer analysis, virtual layup modelling, materials preparation. It comprehensively describes the state-of-the-art modern process featuring all technological equipment that facilitates the efficient and certifiable manufacturing. Important parameters of fabric for the producibility are presented. The article presents flat patterns creation, presumption of potential problems at work, as well as important parameters for the producibility check. Functions that make manufacturing department's (M&P) life easier are brought closer. Different software is named in the article, one is chosen as an example in the article and guided through.
Artykuł opisuje jak komputerowa definicja struktur kompozytowych w modelu CAD upraszcza proces wytwórczy oraz przyczynia się do uzyskania najwyżej jakości owych struktur. Zaprezentowana została ewolucja procesu wytwarzania struktur z uwzględnieniem anizotropowych i warstwowych właściwości kompozytu. Krok po kroku ukazany jest proces projektowania części kompozytowych włączając w to definiowanie kompozytu w modelu komputerowym, symulacje technologiczności, uzyskiwanie płaskich kształtów poszczególnych warstw i transfer wyników na produkcję. Kompleksowo opisany został stan techniki, oprogramowanie i przyrządy konieczne by w sposób nowoczesny produkować wysokiej jakości części. Odpowiednio przygotowany przez konstruktora proces jest wielkim ułatwieniem podczas wytwarzania co w jasny sposób zostało ukazane w niniejszym artykule.
Źródło:: Prace Instytutu Lotnictwa; 2016, 4 (245); 70-78
0509-6669
2300-5408
Pojawia się w:: Prace Instytutu Lotnictwa
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Determination of In-Plane Shear Properties of Laminate with V-Notch Rail Shear Test and Digital Image Correlation
Autorzy:: Karny, Maciej
Powiązania:: https://bibliotekanauki.pl/articles/36405939.pdf
Data publikacji:: 2019
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: digital image correlation
in-plane shear
thermoplastic laminates
v-notch rail shear
Opis:: This article presents the results of the application of Digital Image Correlation (DIC) to measurements of in-plane shear modulus and strength of three different carbon fiber reinforced laminates. Three different approaches to shear strain calculations via DIC are evaluated and compared with standard strain gage measurements. Calculation of shear strain based on averaging DIC strain values of strain gages area in most cases yielded results closest to strain gages, while measurements based on single point strain measuring differed the most from strain gages. These results are attributed to shear strain distribution in the center area of the specimen. Thermoplastic matrix fabric reinforced composite had the lowest shear strength at 5% of shear strain, but the highest ultimate shear strength and strain at failure. Of thermosetting materials, laminate reinforced with unidirectional carbon fiber had shear modulus about 10% lower, than fabric reinforced laminate, but higher ultimate strength and strain at failure. This behavior is attributed to the presence of weaves in fabric reinforcing the laminate, causing shear stiffening of the material, but lowering its ability to deform under shear loading.
Źródło:: Transactions on Aerospace Research; 2019, 3 (256); 57-65
0509-6669
2545-2835
Pojawia się w:: Transactions on Aerospace Research
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

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

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