Application development for calculation of carrying abilities of various string armored aircraft modules

The aircraft module is made by aluminum thin cylindrical body. The module armored by number of strings. Top side of module under cargo of mass. Bottom side is supported by rigid base which loaded by the vertical acceleration.

Scheme of aircraft module and loading.

This task is made like ANSYS macro file and fully parameterized. It is possible to vary number of armor strings, diameter of module, its height, wall thickness, material properties, cargo mass and base acceleration.

Solution achieved by nonlinear LS-DYNA solver and macro produce animation file of deformation process which shown below.

Process of deformation of the armored aircraft module. Process of loosing stability, but module still ability for working.

This is simple example of using ANSYS/LS-DYNA for parameterized calculation, which can widely use in aerospace industry.