With an expansive database of composite materials, Helius Composite software can help you simulate the material behavior of compound components. Built-in solvers minimize the need to have secondary finite element analysis (FEA) software to analyze material characteristics more quickly.
Helius Composite software offers detailed information on composite material behaviour without the complexities of finite element analysis. Use Helius Composite to easily integrate materials into your Digital Prototyping process.
Helius Composite 2017 Portable
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Discover how Helius Composite software can help you streamline composite engineering and manufacturing processes. Use customizable libraries, analysis tool sets, and reporting features to build, explore, and analyse the behaviour of composite materials, laminates, and simple structures.
Firehole Composites (formerly Firehole Technologies, Inc.) was a supplier of computer-aided engineering (CAE) software and consulting services specializing in analysis of composite materials. Founded in 2000, the company's mission is to provide enabling technologies to further the widespread use of composite materials. Their products include Helius:MCT (a multiscale simulation tool for composite progressive failure analysis), Helius:CompositePro (a classical laminate theory and simple structural analysis tool), Helius:MatSim (an online micromechanics lamina simulator), and Prospector:Composites (an online composite material properties database hosted by IDES Inc.).
Firehole Composites began in the academic research of composite material analysis during the mid-1990s. The core technology was part of an academic research project underway in the Mechanical Engineering Department of the University of Wyoming. In 2000, a number of graduate students and faculty at UW saw the commercial potential of the technology and founded Firehole Composites. Firehole Composites continues a collaborative relationship with the University of Wyoming and sponsors ongoing research into composite analysis technology.
Since 1996, CompositePro has been a tool that engineers have used to improve their design of composite laminates. CompositePro provides fast and easy access to a multitude of composite analysis tools based on Classical laminate Theory (CLT), micromechanics and leading failure criterion. It includes engineering tools for plate, tube/beam, and sandwich panel analysis including vibration, buckling, stability and bending.
Hello all, I would like some help on how to define material properties of G40-800-24K reinforced epoxy Cytec 5276-1 for a delamination project that I am doing. I have the mechanical properties of the composite but from watching videos it seems I need the (Lamina) engineering constants of this material for ABAQUS.
i am using abaqus 6.13-4 and composite simulation analysis15. but, while composite simulation analysis15 installation completes it says you have no compatible version af abaqus and it does not appear in abaqus plug-ins . how do i get the compatible version of either abaqus or composite simulation analysis softwares
In general, the failure theories included in Abaqus (Max Stress and Max Strain, or Tsai-Wu and Tsai-Hill models) are not based on the individual constituents and result in poor prediction. Therefore, in this work, an Autodesk add-on for the simulation of composite analysis called Helius PFA (Progressive Failure Analysis) [23] was attached to the Abaqus model to predict the damage in the composite structures. This plug-in helps to incorporate the constituent (matrix and fiber) level failure initiation criteria like MCT (Multi continuum theory) based failure [24], Christensen [25], Puck [26] and LaRC02 [27] into the Abaqus software (Dassault systems, v6.13, SIMULIA, Johnston, RI, USA). Helius PFA uses separate material manager to include the composite lamina properties. Based on the input provided to the material manager, Helius PFA provides the constitutive relations for composite materials as per the required failure theory to the Abaqus input. As seen in Table 1, the lamina material properties were derived from the individual material properties input (fiber and resin properties) given to the material manager of Helius PFA.
Individual plies were defined under a composite layup sequence with orthotropic non-linear elastic material properties based on experimental measurements. Experiments were conducted on the same material to determine the maximum tensile, compressive and shear strength properties. The detailed material properties used for the model are listed in Table 1, Table 2 and Table 3. Based on the LaRC02 failure criterion under uniaxial compression loading: (1) Fiber failure is further divided into (1.a) fiber compressive failure with matrix compression, and (1.b) fiber compressive failure with matrix tension. (2) Matrix cracking is again divided into (2.a) matrix cracking in tension, and (2.b) matrix cracking in compression. For the current model, due to the presence of fiber waviness imperfections in the cured laminate, it was assumed that majority of failure progression occurred due to fiber kinking. The fiber compression failure scenario was explained due to the collapse of fibers subjected to initial misalignment, leading to shear kinking and further extending to the supporting matrix [29,30].
A better understanding of the effect of impact damage on composite structures is necessary to give the engineer an ability to design safe, efficient structures. Current composite structures suffer severe strength reduction under compressive loading conditions, due to even light damage, such as from low velocity impact. A review is undertaken to access the current state-of-development in the areas of experimental testing, and analysis methods. A set of experiments on Nomex honeycomb core sandwich panels, with thin woven fiberglass cloth facesheets, is described, which includes detailed instrumentation and unique observation techniques. These techniques include high speed video photography of compression after impact (CAI) failure, as well as, digital image correlation (DIC) for full-field deformation measurements. The effect of nominal core density on the observed failure mode is described. A finite element model (FEM) is developed to simulate the experiments performed in the current study. The purpose of this simulation is to predict the experimental test results, and to conrm the experimental test conclusions. A newly-developed, commercial implementation of the Multicontinuum Failure Theory (MCT) for progressive failure analysis (PFA) in composite laminates, Helius:MCT, is included in this model. The inclusion of PFA in the present model gives it the new, unique ability to account for multiple failure modes. In addition, significant impact damage detail is included in the model as a result of a large amount of easily available experimental test data. A sensitivity study is used to assess the effect of each damage detail on overall analysis results. Mesh convergence of the new FEM is also discussed. Analysis results are compared to the experimental results for each of the 32 CAI sandwich panel specimens tested to failure. The failure of each specimen is accurately predicted in a high-fidelity, physics-based simulation and the results highlight key improvements in the understanding of honeycomb core sandwich panel CAI failure. Finally, a parametric study highlights the strength benefits compared to mass penalty for various core densities.
A composite consists of a resin , or plastic, with fiber added to prevent stretching or breaking. Composites are used for liquid-oxygen tanks because they are much lighter than metals, but they are flammable and thus need metal liners to prevent any chance of ignition, Pournelle said.
In addition to adding weight to the tank, the metal liner shrinks at a different rate than the composite material when exposed to cold temperatures. When tanks are filled with liquid oxygen, the composite and liner can separate, and so an extra support structure must be added to compensate, Pournelle said. 589ccfa754
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