CODA Audio EASE Focus 3 is a three-dimensional, acoustic simulation software for the configuration and modeling of line array systems and of adjustable loudspeakers, such as digitally steered columns. EASE Focus 3 is free for the end user.
Great efforts have been made to keep EASE Focus 3 intuitive and easy-to-use while introducing three-dimensional coordinates and many new features. It can be considered a tool for both the end user, who needs to set up the sound system for a show, as well as for the R&D engineer, who is interested in the acoustic qualities of the array design.EASE Focus 3 is the optimal tool for easy and quick prediction of the sound system performance in a given venue. Compared to conventional aiming software the applicability of EASE Focus 3 is much larger. It is not fixed to a single loudspeaker product.
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The aim of this study was to investigate the applicability of acoustic emission (AE) technique to evaluate delamination crack in glass/epoxy composite laminates under quasi-static and fatigue loading. To this aim, double cantilever beam specimens were subjected to mode I quasi-static and fatigue loading conditions and the generated AE signals were recorded during the tests. By analyzing the mechanical and AE results, an analytical correlation between the AE energy with the released strain energy and the crack growth was established. It was found that there is a 3rd degree polynomial correlation between the crack growth and the cumulative AE energy. Using this correlation the delamination crack growth was predicted under both the static and fatigue loading conditions. The predicted crack growth values was were in a good agreement with the visually recorded data during the tests. The results indicated that the proposed AE-based method has good applicability to evaluate the delamination crack growth under quasi-static and fatigue loading conditions, especially when the crack is embedded within the structure and could not be seen visually.
Acoustic emission (AE) is a naturally occurring phenomenon, which is the result of transient elastic wave propagation caused by a sudden release of energy inside the material [20]. There are various sources of AE events in composite materials such as matrix cracking, fiber/matrix debonding, fiber breakage, etc. [21,22,23]. Recently, AE has been utilized as an applicable technique to detect in-situ information from the damages that occur in laminated composites [5, 24,25,26,27].
The aim of this paper is to investigate the delamination propagation in glass/epoxy composites under mode I quasi-static and fatigue loading conditions. The article is composed of two sections. In the first section, the delamination behavior under quasi-static loading condition is investigated using the mechanical and AE data. Then, the correlations between AE energy, the released strain energy and the crack growth are established theoretically and it is found that there is a 3rd degree polynomial correlation between the crack growth and the cumulative AE energy. Then, quasi-static delamination growth was predicted using the obtained correlation and the obtained AE signals. In the second section, the delamination crack growth under fatigue loading is predicted using the same concept as the static loading. The advantage of the proposed method is prediction of delamination crack growth using only one AE sensor without any need to determine AE wave propagation speed in the specimens. Consistency of the AE-based evaluated results and visually recorded values illustrates that the proposed AE method is more suitable than the conventional methods for detection of delamination crack growth in the laminated composites under quasi-static and fatigue loading conditions.
The experimental work was carried out on laminates fabricated from an epoxy resin reinforced with unidirectional and woven E-glass fibers with the density of 1.17 \(\hbox g/cm^3\), 390 and 300 \(\hbox g/m^2\), respectively. The laminates were prepared by hand lay-up method. The starter crack was formed by inserting a Teflon film with a thickness of 20 \(\upmu \)m at the mid-plane during molding as an initial crack for the delamination. The laminated composite specimens consist of ten plies with a rectangular shape and uniform thickness. Characteristics of the specimens used for this study are illustrated in Fig. 1. For ease of use, the unidirectional specimen is called U and the woven specimen is called W.
The following results, i.e. figures, tables, etc., are only related to the AE signals originated from delamination damage that are discriminated from the other damage mechanisms. Figure 8 shows load and cumulative AE energy of delamination versus displacement curves for the \(\hbox U_\mathrmS1\) and \(\hbox W_\mathrmS1\) specimens. In consistency with the crack growth curve in Fig. 3, each pop-in in the load curve is related to a sudden crack growth which is accompanied by a well-defined acoustic energy jump. By applying the load to the specimen, as long as the crack is arrested, the strain energy is stored in the specimen. When the stored strain energy reaches to its critical value, the crack propagates and the stored strain energy is released (see Fig. 9). According to Fig. 9, released strain energy at each pop-in (\(\hbox dU \big _\Delta )\), can be calculated by Eq. (1) [47]:
Figure 10 illustrates the correlation between the AE energy jump and the released strain energy at the pop-ins. In consistent with Eq. (2), there is a linear relationship between the AE energy jump and the released strain energy. Thus, amount of the AE energy, induced by the crack growth, is a function of the released strain energy.
where B, P, a, E, U, and h are the specimen width, applied load, initial crack length, young modulus, released strain energy, and a half thickness of the specimen, respectively. Thus, the elastic strain energy (\(\Delta U)\) released due to growth of delamination length (\(\Delta a)\) is calculated as follows:
The aim of this study was to investigate the delamination propagation in glass/epoxy composites under mode I quasi-static and fatigue loading conditions. The results are represented in two sections. In the first section, correlations among the AE energy with the released strain energy and the crack growth were established based on the theoretical fundamentals. It was shown that there is a 3rd degree polynomial correlation between the cumulative AE energy of delamination and the cumulative crack growth and accordingly the quasi-static delamination crack growth was predicted using the AE method. In the second section, the delamination crack growth under the fatigue loading is predicted using the proposed AE method. The proposed AE method has some advantages such as predicting delamination growth using only one AE sensor without a need to determine AE wave propagation velocity in the specimens. This method is a robust technique for detecting and measuring the crack length, especially when the crack is hidden and could not be seen visually.
The EASE software suite provides system designers and consultants with an invaluable set of tools for all aspects of professional practice, from detailed, realistic modeling and simulation of venue acoustics and sound system performance to informative and engaging client presentations, as well as professional data assessment and verification.
The d&b ArrayCalc simulation software is the simulation tool for d&b line arrays, column and point source loudspeakers as well as subwoofers. This is a comprehensive toolbox for all tasks associated with acoustic design, performance prediction, alignment, rigging and safety parameters. For safety reasons d&b line arrays must be designed using the d&b ArrayCalc simulation software. d&b ArrayCalc is available as a native stand-alone application for both Microsoft Windows and macOS operating systems. This can significantly reduce setup and tuning time in mobile applications and allows for precise initial simulations when planning installations. Listening planes can be defined in the venue tab, creating a three dimensional representation of any audience area in a given venue.
One of the first experimental determinations of the CTOA was mentioned by Luxmoore et al. [7]. Using centre notched and double-edge notched specimens of aluminium alloy, they measured the CTOA during stable crack growth. They noted that the crack tip opening 8 varied linearly with increases in crack length. This linear behaviour indicated that the CTOA remains constant and equal to 2.1. This was also previously noticed by de Koning et al. [8].
Conditions of stable crack growth require that the rate of change of the crack driving force with increasing crack length Aa is smaller than the increase of crack growth resistance expressed in terms of crack opening displacement:
The CTOA fracture criterion has now become one of the most promising fracture criteria used for characterizing stable tearing in thin metallic materials. Initially, fracture resistance to crack extension was given by Charpy energy, as in the Battelle two-curves method (BTCM) [13]. The Charpy test is related to crack initiation, bending of the specimen, and plastic deformation at the load points. It is necessary that tests performed to characterize the propagation resistance be able to isolate and quantify the propagation energy with respect to incremental crack advance. For this reason and due to the development of higher strength steels with increased toughness and lower transition temperatures by using controlled rolling techniques, Charpy energy was replaced by drop-weight tear test (DWTT) energy in the HLP two-curve method [14]. DWTT tests are also related to crack initiation, bending of the specimen, and plastic deformation. However, notched DWTT specimens are larger
than Charpy ones and therefore relatively less of the total fracture energy is related to initiation. The statically pre-cracked DWTT showed the best compromise between isolating the propagation energy and ease of specimen preparation. Another step was the development of a test methodology to indirectly measure CTOA, derived on the basis of the difference in energy between two modified DWTT specimens with different initial crack lengths [15]. 2ff7e9595c
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