eLamX²

Version 3.0.0 (15.02.2025)
Windows Installer
Windows ZIP file (no installation required - extract and run the executable in the "bin" directory)
Linux-AppImage
Linux ZIP file (no installation required - extract and run the executable in the "bin" directory)
MacOS ZIP file (no installation required - extract and run the executable in the "bin" directory)

eLamX² at GitHub

Wiki
Installation Instructions
Tutorialvideos (German)

Overview

eLamX² is a OpenSource, Java-written composite calculator, which is being developed at Technische Universität Dresden, Institute of Aerospace Engineering, Chair of Aircraft Engineering. Calculations are based on the classical laminated plate theory. At present modules for composite calculation including hygrothermal effects, failure analysis and engineering constants, stability and deformation analysis of composite plates, comparison of a multitude of failure criteria and the World-Wide Failure Exercise are implemented. Additional modules dealing with micromechanics, nonlinear calculations, sandwich structures and composite plate vibration are planned or under development.

Easy laminate build-up

mouse-controlled laminate build-up
can be modified at will
easy input of symmetrical laminates
build-up apparent at all times

Laminatinformationen

ABD-Matrix in Tabellenform (kopierbar)
inverse ABD-Matrix in Tabellenform (kopierbar)
Ingenieurskonstanten
Hygrothermale Eigenschaften

Composite calculation

ABD-matrix
strains and stress resultants
thermal and hygroscopic effects
layerwise local strains and stresses
factor of safety for each ply including failure mode
export

Stability

for symmetrical laminates (D16, D26 ≠ 0 as well)
bending-twisting coupling terms D16, D26 can be set to zero for comparison with analytical solutions
rectangular plate with arbitrary boundary conditions (hinged, clamped, free)
all in-plane loads (nx, ny, nxy)
maximum number of half waves adjustable between 1 and 20
consideration of stiffeners
3D-display of buckling modes
png export

Deformation

for symmetrical laminates (auch D16, D26 ≠ 0)
rectangular plate with arbitrary boundary conditions (hinged, clamped, free)
constant surface pressure on the entire plate domain
maximum number of half waves adjustable between 1 and 20
consideration of stiffeners
3D-display of deflection
local stresses and strains of each layer as contour plot
visualization of failure locations
png export

Stacking Sequence Optimization

for symmetric and non-symmetrc Lay-Ups
Strength and Buckling Constraints
Optimization based on genetic Algorithms
discrete Layer Angles

Failure criteria

3D display (Puck, ZTL, Hashin, Tsai-Wu, Mat58-LS-Dyna, max. stress, Cuntze, Edge, Rotem, Sun, Mayes)
for arbitrary strength values
superposed display possible
raw data export
png export

Failure body for composite laminates

3D display of laminate failure body using first ply failure criterion (Puck, ZTL, Hashin, Tsai-Wu, Mat58-LS-Dyna, max. stress, Cuntze, Edge, Rotem, Sun, Mayes)
for arbitrary strength values
for self-defined laminates
raw data export
png export