Laminator  Crack + License Code & Keygen
Laminator Activation Code is a program for the prediction of laminated composite ply properties. It is available for free on the web at www.cns.fr/~abd or by e-mail at abd@cns.fr
Application fields include structural analysis, design, manufacturing process control, and evaluation of 3D printed products.
Laminator is an engineering software program that analyzes laminated composite plates according to classical laminated plate theory.
Input consists of ply material properties, material strengths, ply fiber orientation and stacking sequence, mechanical loads and/or strains, and temperature and moisture loads.
Output consists of apparent laminate material properties, ply stiffness and compliance matrices, laminate "ABD" matrices, laminate loads and mid-plane strains, ply stresses and strains in global and material axes, and load factors for ply failure based on Maximum Stress, Maximum Strain, Tsai-Hill, Hoffman, and Tsai-Wu failure theories.
Loads for laminator:
Pulleys:
- Types of pulleys: (Internal, External and Circular)
- Types of mechanics: (circular, linear, pivoting, angles)
- Fixed/moving pulley ratio
- Number of cycles
- Pitch radius of the external/internal pulley
- Pitch radius of the circular pulleys
- Number of full turns of the external pulleys
- Number of full turns of the internal pulleys
Laminates:
- Type of laminates: FGCM, FDM, FGM, FGFM
- Number of plies
- Thickness of laminates
- Stacking sequence of plies
- Pitch ratio between plies
- Number of ply groups, e.g. SP, ST, LP
- Pitch ratio between ply groups
- Number of ply cross-sections within a given ply group
- Thickness of ply cross-sections within a given ply group
- Number of given ply cross-sections within a given laminate
- Minimum outer layer thickness of the laminate (except FDM)
Output:
- Apparent ply stiffness (MPa)
- Apparent ply compliances (MPa)
- "ABD" ply matrix (MPa)
- Loaded ply mid-plane strain (MPa)
- Loaded ply end-side strain (MPa)
- Loaded ply mid-plane stress (MPa)
- Loaded ply end-
Laminator  Activation Code
Use of this software is aided by existing software programs like:
Teststresstest
and
Ziomechanics
to analyze the input material properties, as well as the 3D Format input spec from PlyPrism.
The program's user interface allows it to read input plate data from other software programs. For example, it can read ply material properties from other programs such as Systresstest, Teststresstest, PlyPrism, and QUAPEAK.
The program can be used for analysis of "stressed" or "unstressed" plates. Unstressed plates (per ZiaHanson) will also be analyzed using the input plate format from 3D Format.
Compatible with US and International standards for failure criteria, design methodologies, and design codes.  The input plate format from PlyPrism is compatible with both the 3D Format format and the Standard Laminates format.  Output (ASCII) plate files from the program are compatible with standard plate output formats.
Formal deflection
Contour integration
Laminates
Continuous stress-strain
Continuous modulus of elasticity
Buckling analysis
Continuous stress-strain from global stress
continuous modulus of elasticity
Continuous modulus of elasticity
Buckling analysis
Continuous modulus of elasticity
Continuous strain
Continuous strain
Ductile vs. brittle analysis
Continuous modulus of elasticity
I.. General Features
The aim of Laminator is to provide an efficient and accurate means for analyzing composites (laminated plates) under complex loading conditions using the appropriate theoretical model, while taking into account the ply level material and geometric nonlinearities.
Laminator is designed to analyze plate-like structures. Therefore, it is not applicable for analyzing single or multi-point bending, buckling, and impact of plates.
The software is based on a formal expansion of composite materials in the form of a laminate, taking into account geometric, mechanical, and thermal non-linearities. At each stage of the analysis, the differential displacement
Theory
Coefficients
Failure mode
Folding
Diffusing boundary conditions
Gauge space
Global axial load
Global plane strain
Hoffman and/or Tsai-Wu failure theories
Laminates
Material properties
Material properties and boundary conditions
Nonlinear conversion from displacement to axial stress
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