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EN
The widespread use of perforated vibrating surfaces in various industries requires maximum productivity and construction reliability. The research task is to determine the significant factors and their degree of influence on the natural oscillations of vibrating surfaces with multiple holes of complex geometry. For this purpose, studies were carried out for three samples of plates: non-perforated, with basic round holes and holes of complex geometry in the form of a five-petal epicycloid. Studies of the natural oscillations of perforated vibrating surfaces have been conducted using the finite element method in Abaqus, which has proved sufficient accuracy of calculations. The dependencies of the natural oscillation frequency of perforated surface samples on their thickness, partition width between the holes, material type, and fixing method have been obtained. In addition, the analysis involved the study of eight modes of oscillation common in practice. The dependencies of the natural oscillation frequency of perforated surface on the relative parameters of ligament efficiency and stiffness coefficient have also been obtained. These parameters take into account the ratios of the partition width between the holes to the plate thickness and the dimensions of the holes. The research results allow to obtain levels of influence of the perforated vibrating surface parameters on their natural oscillations frequency. The obtained research results make it possible to further determine the absence of damage between the holes and predict the durability of perforated vibration surfaces in the presence of holes of complex geometry.
EN
A set of experiments having in target determination of fracture resistance was performed on the Fiber Reinforced Polymer (FRP) composites specimens with an additional monitoring of damage onset and evolution with a so-called Acoustic Emission (AE) technique. The AE technique is a non-destructive material testing method, which enables registering the phenomena usually not audible with a human ear - the frequency bands lay between 100 and 1000kHz. For the FRP composites this enables monitoring various damage phenomena - matrix cracking, delamination, fiber cracking etc. by acquisition and subsequent analysis of several AE parameters: number of hits, number of counts, amplitude or energy of the signal. In the paper advantages of a deeper analysis of the raw AE signal was presented with an application of the Fast Fourier Transform (FFT), leading to a more detailed damage identification along the whole loading procedure. The study proved the usability of the AE method in damage monitoring of the FRPs; a bundle of illustrative examples of chosen acoustic emission parameters’ evolution displayed on the background of the load applied to composite specimens was presented and interpreted.
EN
This paper aims at experimental research of the effect of hybrid interface (carbon/glass fibers) on delamination resistance in unidirectional fiber reinforced polymer (FRP) composite laminates under the mode I opening load conditions. Three group of laminates exhibiting different combinations of reinforcing materials at delamination plane were tested. Critical strain energy release rates were determined by using the double cantilever beam (DCB) tests in accordance with the ASTM D5528 Standard. Values of the GIC were calculated by using classical data reduction schemes and they were compared with values obtained by using an alternative compliance based beam method (CBBM). For precise detection of delamination onset all tests were additionally supported by registration of the acoustic emission (AE) signal. Contribution of mixed-modes were evaluated by using numerical finite element analysis. Obtained outcomes revealed, that differences in the mode I c-SERR values obtained by using four different methods were insignificant. Moreover, the greatest value of the GIC was determined for laminates with hybrid interface and it was equal 0.24 N/mm.
EN
The paper presents a study on influence of different fabric weave and fabric orientation on strength properties of fiber reinforced polymer composites. The research concerns materials used in a new type of rotorcraft. Four series of laminates were fabricated with hand forming, using the MGS L285/H285 epoxy resin. Triple-kind experiments were performed: the Shore hardness measurements, tensile strength testing and fractographic analysis. The specimens of different series shown various strength and stiffness characteristics, depending on the type of weave and fabric layup. Three different failure schemes were observed. The Poisson coefficient was different among series, as well, but no understandable link to specimen morphology could be found so far. Fractographic observations suggested intralaminar delamination.
EN
The paper investigates the growing popularity of composite materials concentrating on explanation of their advantages, especially taking into consideration composite materials used in the aerospace industry such as polymer matrix composites, metal matrix composites, ceramic matrix composites and smart composite materials. Various types of matrices and fibers are described with special emphasis on nanotechnology and opportunities to improve the properties of composites. The paper also presents selected examples of applications in the aerospace industry.
EN
The paper investigates experimental results of static and dynamic fracture toughness. The three-point bending test and the Charpy pendulum test were performed for two kinds of polymers: Epidian 5 epoxy resin cured with Z1 curing agent and Epidian 53 epoxy resin cured with Z1 curing agent. The comparison between the values of a maximum static and a maximum dynamic force are discussed as well as the values of static and dynamic fracture toughness, with special emphasis on microscopic views of crack propagation.
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