Fig. 1.
Fig. 2.
Grumman Seaplane (G-73/G-73T Wing Box Component) [17].
Fig. 3.
Model of a weak microvolume under loading and after unloading (explanations in the text) [21,22].
Fig. 4.
Example of delamination and approximate linear size in relation to the initial damage width.
Fig. 5.
Damage to an aircraft flap element, before and after preparation for repair.
Fig. 6.
Point defects.
Fig. 7.
Core alignment for the panel in sandwich.
Fig. 8.
Numerical values of nodal points in each row of a honeycomb fragment
Fig. 9.
Calculation of the Poisson distribution function and mapping to honeycomb nodes in the Excel model.
Fig. 10.
Example visualization of simulated delamination spreading across honeycomb cells.
Fig. 11.
Regular initialization estimation program.
Fig. 12.
Universal propagation time.