Wszystkie pola: metal composite - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Numerical analysis of the metal-composite joints
Autorzy:: Derewońko, A.
Cielęta, R.
Powiązania:: https://bibliotekanauki.pl/articles/243344.pdf
Data publikacji:: 2008
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: metal-composite joint
FEM
contact problem
nonlinearity
aircraft structure
Opis:: The development and implementation of the new technologies and materials are one of the conditions allowing improving the aircraft structures. The composite materials enable to reduce the aircraft weight and keep appropriate strength and fatigue properties. Application of the composite materials in the wing elements, and metal alloys in assemblies of the aircraft fuselage requires elaboration of the appropriate method for technology joining metal and composite. Bonding eliminates breakages in the composite plies which are initiated during assembly process of the structure with mechanically fastened joints e.g. bolts [1]. The strength and stiffness of the composite depend on shape and direction of the fibre which carry the tensile and compression stresses. Shear stress and strength of the composite depend on the resin system. Therefore, the use of composites brings more complicated design approach compare to metal. The aim of the study is tofind appropriate method to determine the failure loading of the metal-composite aircraft wing pivot fitting. Numerical and laboratory investigations for metal-composite joints are presented. Interaction between the composite plies is modelled as the contact problem. It allows determining the strain and stress at the contact surfaces and stress concentration fields. Contact modelling technique is also applied to model interface between metal and composite. Engineering approach to the model full-scale co-curing triple stepped lap joint is presented. The professional engineering software tools are used to create accurate models. Tensile tests of the metal-composite joint were carried out to verify the numerical analysis methods.
Źródło:: Journal of KONES; 2008, 15, 1; 39-50
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: About mechanical joints design in metal - composite structure
Autorzy:: Puchała, K.
Szymczyk, E.
Jachimowicz, J.
Powiązania:: https://bibliotekanauki.pl/articles/246795.pdf
Data publikacji:: 2012
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: mechanical joint
adhesive joint
FEA
aviation
Opis:: Riveting is still one of the main joining methods of thin-walled aircraft structures. Such features as simplicity of implementation, possibility of two different material connection (e.g. metallic with non-metallic ones) and the fact that is it a well-known (reliable) method causes popularity of riveting. The never-ending attempt to obtain as low mass as possible (mainly to reduce fuel consumption) is the reason for using material of high specific strength in the aerospace industry. High strength titanium or aluminium alloys (e.g. 2024T3) and composite laminates (e.g. CFRP or Glare) are examples of such materials. The article deals with methods of connecting various materials. The paper presents advantages and disadvantages of different/selected connection types. Strength prediction and failure modes of mechanical joints are described for metallic as well as for composite components. Composites are complex materials having an anisotropic structure (and anisotropic mechanical properties) leading to various failure mechanisms. Main principles for appropriate joint design of composite laminate panels (laminate configuration and typical/specific geometrical dimensions) are indicated/specified. The bearing failure mechanism is accepted to be a safe progressive one. Mechanism of bearing (generally compressive) load transfer into composite laminates by shear of the matrix is analysed. Some examples of improvement bearing strength of laminates are presented according to literature. On the base of presented examples and bearing load transfer analysis, some conclusions for an appropriate solution of this problem are drawn.
Źródło:: Journal of KONES; 2012, 19, 3; 381-390
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Analysis of selected parameters influence on failure in metal-composite mechanical joint
Autorzy:: Puchała, K.
Powiązania:: https://bibliotekanauki.pl/articles/242244.pdf
Data publikacji:: 2014
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: mechanical joint
CRFP
aviation
FEM
Opis:: The never-ending attempt to obtain as low mass as possible is the reason for using material of high specific strength (stiffness) in the aerospace industry. High strength titanium or aluminium alloys (e.g. 2024T3) and composite laminates (e.g. CFRP or Glare) are the examples of such materials. Despite a large number of composite types, fibre reinforced composites in the form of laminates are commonly used in aircraft structures. One-half of modern aircrafts is made of composites. However, the second one is still made of metallic alloys. The usage of different materials in aircraft structures results in the necessity of joining composite and metallic components. There are three connection methods for aircraft primary structures: mechanical (riveting, bolting), adhesive (bonding) and hybrid where both mentioned methods are used. The paper deals with metal-composite mechanical joint. Although fibre reinforced composites have high tensile strength, the load transfer in mechanical joints of such components is limited. Strength of composite laminates is dependent on the joint geometry; however, it is strongly influenced by laminate lay-up. There are five global failure modes for mechanically fastened composite laminates: tension, bearing, shear-out, cleavage and pull-through. The bearing failure mechanism is a safe progressive mechanism not leading to catastrophic failure and therefore it is acceptable. Problems with strength assessment of composite mechanical joints are drawn. Some geometrical (joint width), material (bolt material, stacking sequence) as well as numerical parameters (failure criterion) are analysed.
Źródło:: Journal of KONES; 2014, 21, 1; 223-232
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Selected problems of electrical discharge machining (EDM) of metal composite materials applied in manufacturing of mechanical vehicles
Autorzy:: Perończyk, J.
Powiązania:: https://bibliotekanauki.pl/articles/244481.pdf
Data publikacji:: 2011
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: vehicles
metal composite materials
electrical discharge machining (EDM)
electrical discharge cutting (WEDM)
surface layer (SL)
Opis:: The paper presents examples of applications for metal composite materials on Al matrix reinforced with ceramic particles in the form of grains, fibre or whiskers in the automotive industry. Highlighted are the advantages and drawbacks of such composite materials and issues involved in shaping complete parts. Presence of hard and brittle ceramic particles in the Al alloy (given their sufficient concentration) significantly impacts on the physical, chemical and mechanical properties of the material and its suitability for shaping complete parts and constituting a surface layer (SL) with required properties. In making metal composite materials of Al alloys, various (including the latest) methods of casting are applied, often in combination with press molding in semi-fluid state, as well as powder metallurgy (P/M) methods. The final machining of functionally significant surfaces is done by machining (by all ways and variants). With presence of more than 5% (by volume) ceramic reinforcing particles it becomes necessary to use cutting blades of the so-called super hard materials, including composites of polycristalline diamond and diamond. This considerably increases manufacturing costs. Electrical discharge machining has proved to be an effective way for shaping metal parts, in all its variants: sinker (EDM), wire erosion (WEDM), micromachining (ěEDM), shaping by free electrode (REDM), discharge grinding (AEDM) and other. Cited in the paper are the results of own research connected with EDM and WEDM of Al alloys composite cast and reinforced with particles of Al2O3 (AlSi7Mg + 20%Al2O3) and a composite material produced by powder metallurgy methods (P/M) reinforced with various (maximum 10%) concentrations of Al2O3 or SiC or Si3N4. EDM and WEDM technological characteristics were defined for the studied materials in the form of regressive dependencies as statistical models of given indicators allowing for defining impact of machining parameters on shaping the indicators. In addition, there are selected photos of metallographic structures, enabling observation and evaluation of surface layer phase changes and chemical composition after EDM. The highly enlarged SEM micro-photos which are included show the geometric structure of machined surface, micro-cracks on borders of the composite material grains, presence of minor reinforcement particles adhering to the surface. This confirms the complex nature of electrical discharge machining mechanism taking place locally after very high temperatures and in a very short time, in presence of cold dielectric.
Źródło:: Journal of KONES; 2011, 18, 1; 429-442
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Modified hagg and sankey metod to estimate the ballistic behaviour of lightweight metal/composite/ceramic armour and a fuselage skin of an aircraft
Autorzy:: Klimaszewski, S.
Woch, M.
Powiązania:: https://bibliotekanauki.pl/articles/247835.pdf
Data publikacji:: 2012
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: reliability
ballistic shield
bullets perforation
Opis:: Hagg and Sankey method assesses the functionality of containment rings, which prevent perforation of an aircraft's elements from turbine engine disc fragments after disc burst. However, the method assumption was based on studies of mechanism of destruction of ballistic shields made of among others ceramics, by small arms bullets. The hard ceramic facing of the ballistic shield blunts the projectile and breaks up the projectile's hard core used for armour piercing. As an impact result, a conoid of finely pulverized ceramic dust is formed, absorbing energy in the formation process. The dust, containing the remnants of the projectile's energy hits the backing, but is now spread over a larger area. With backings made of fibre, energy is absorbed in stretching, breaking and delamination. With backings made of ductile metal, energy is absorbed in elastic deformation. Modification of the method consisted of taking into account the stratification of the ceramic-metal composite and the occurrence of an aircraft stiffened skin, in order to better assess the effectiveness of ballistic shields. The concept of estimating the resistance was based on the described destruction mechanism, where the object of analysis is a metal containment ring with an additional ceramic protective ballistic shield. A comparison of two scenarios- with and without an additional 2 mm aluminum alloy skin was taken into account. For this particular scenario, results were sufficient for both of the two analyzed endurance criteria.
Źródło:: Journal of KONES; 2012, 19, 2; 245-252
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Wybrane zastosowania kompozytów w wojsku
Selected applications of composites in the military
Autorzy:: Błachnio, Józef
Chalimoniuk, Marek
Nidzgorska, Adrianna
Powiązania:: https://bibliotekanauki.pl/articles/38952238.pdf
Data publikacji:: 2023
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: kompozyt metalowy
kompozyt polimerowy
kompozyt ceramiczny
metal composite
polymer composite
ceramic composite
Opis:: W artykule przedstawiono problematykę dotyczącą zastosowania nowych rozwiązań konstrukcyjnych z wykorzystaniem materiałów kompozytowych, na szeroko rozumiane potrzeby wojska. Pokrótce przedstawiono charakterystykę kompozytów i ich właściwości, wyszczególniając ich liczne zalety, a także niedostatki. Omówiono nowe konstrukcje podzespołów samolotów, śmigłowców oraz zasygnalizowano wzrost udziału kompozytów polimerowych w lotnictwie wojskowym i cywilnym. Przedstawiono zastosowanie kompozytów do ochrony żołnierza: elastyczną kamizelkę kompozytową i hełm, do ochrony przed promieniowaniem mikrofalowym, jak również egzoszkielet żołnierza ułatwiający operacje na polu działań. Podkreślono możliwości szerokiego zastosowania materiałów kompozytowych w różnych gałęziach przemysłu.
The article presents the issue of applying new design solutions from composite materials for military needs. The article also includes composites’ characteristics and properties, underlining their benefits and deficiencies. New aircraft and helicopter subassembly designs were demonstrated, and an increased use of polymer composites in civil and military aviation was mentioned. In addition, the application of composites used for the soldier’s protection in the form of elastic composite west, helmet against microwave radiation was depicted, as well as the soldier’s exoskeleton to facilitate operations on the field. Composites are future-oriented materials applied in civil and military areas due to their properties.
Źródło:: Journal of KONBiN; 2023, 53, 4; 191-209
1895-8281
2083-4608
Pojawia się w:: Journal of KONBiN
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 7.

Tytuł:: Numerical calculations of RVE dimensions for two-phase material
Autorzy:: Miedzińska, D.
Niezgoda, T.
Powiązania:: https://bibliotekanauki.pl/articles/242298.pdf
Data publikacji:: 2011
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: microstructure
two-phase material
metal-ceramic composite
RVE
Opis:: A representative volume element (RVE) is a statistical representation of typical material properties. It should contain enough information on the microstructure thereby be sufficiently smaller than the macroscopic structural dimensions. The paper deals with the numerical calculations of the dimensions of the RVE for a two-phase material microstructure. Two and three dimensional models are taken into consideration. The structure of the samples are developed on the base of randomization of elements belonging to one of the phases. The phases volume share is 50/50%. The following series of the models are analyzed: from 10 x 10 to 100 x 100 elements for 2D samples and from 10 x 10 x 10 to 100 x 100 x 100 elements for 3D samples. The element characteristic dimension is 10 jm. The elastic behavior of the base materials (magnesium and alumina) is taken into account. The quasi-static compression tests of the developed structures are carried out with the use of LS-DYNA computer code. The results are presented as the equivalent Young modulus values and compared to the calculations based on the rule of mixtures. The stabilization of the achieved results allows to assess the dimensions of the RVE for two-phase material with random distribution.
Źródło:: Journal of KONES; 2011, 18, 2; 303-310
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 8.

Tytuł:: Numerical analysis of an influence of ceramic plate surrounding by metal components in a ballistic panel
Autorzy:: Stanisławek, S.
Morka, A.
Niezgoda, T.
Powiązania:: https://bibliotekanauki.pl/articles/247100.pdf
Data publikacji:: 2011
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: computational mechanics
ballistic protection
composite armour
ceramics
Opis:: The paper presents a numerical study of the three layer composite panels impacted by an AP (Armor Piercing) 7.62x51mm projectile. The standard panel is built with aluminum and Al2O3 ceramic plate. The studied model, however, consists of the same aluminum plate but the ceramic one is surrounded by a steel packet. The problem has been solved with the usage of the modelling and simulation methods as well as finite elements method implemented in LS-DYNA software. Space discretization for each option was built with three dimension elements guaranteeing satisfying accuracy of the calculations. For material behaviour simulation, specific models including the influence of the strain rate and temperature changes were considered. Steel projectile and aluminum plate material were described by Johnson-Cook model and ceramic target by Johnson-Holmquist model. In the studied panels, the area surrounding back edges was supported by a rigid wall. The obtained results show interesting properties of the new structures considering their ballistic resistance. The ballistic protection of a three layer panel under the WC projectile impact is indentified. Panels containing the ceramic plate surrounded at each side by a steel packet plate are stronger. However, this difference reaches only the level of 2.4% regardless erosion parameters. Definitely technological complication and an area density mass increase cannot balance a small improvement of ballistic protection. However, this kind of panel is not suggested as a useful solution. Further investigations are suggested in order to analyze an influence of initial ceramic compression. The results of those numerical simulations can be used for designing of modern armour protection systems against hard kinetic projectiles.
Źródło:: Journal of KONES; 2011, 18, 4; 471-474
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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