On residual compressive strength prediction of composite sandwich panels after low-velocity impact damage

Abstract

This paper introduces a nonlinear finite element analysis on damage propagation behavior of composite sandwich panels under in-plane uniaxial quasi-static compression after a low velocity impact. The major damage modes due to the impact, including the residual indentation on the impacted facesheet, the initially crushed core under the impacted area, and the delamination are incorporated into the model. A consequential core crushing mechanism is incorporated into the analysis by using an element deactivation technique. Damage propagation behavior, which corresponds to those observed in sandwich compression after impact (SCAI) tests, has been successfully captured in the numerical simulation. The critical far field stress corresponding to the onset of damage propagation at specified critical locations near the damage zone are captured successfully. They show a good correlation with experimental data. These values can be used to effectively predict the residual compressive strength of low-velocity impact damaged composite sandwich panels.

Compression After Impact on Honeycomb Core Sandwich Panels with Thin Facesheets, Part 2: Analysis

“…In one reference [10], they focus on local strain results and comparison to experiment in order to make residual strength redictions. In an earlier attempt [11], the authors had focused on delamination as a failure mode, which is not a topic in the current research.…”

Comparative Geometrical and Experimental Study on a New Sandwich Meta-Structure and its Classic Three-Layer Counterpart

“…However, the existence and possible crushing of the core seems to be the most cumbersome for the following reasons. Firstly, the area of crushed core is the largest, in particular, it is larger than the debond- ing and delamination areas [23]. Secondly, delamination between the plies of laminated facings of a rectangular sandwich panel doesn't need to be dangerous provided that the delaminated facing is not loaded by stretch out-of-plane forces, perpendicular to the plane of delamination [24] and reinforcements of the adjacent, delaminated plies are perpendicular/parallel to the edges of the panel.…”

“…The effects of impact load of sandwich panel with laminate facings and continuous core can be as follows [23]: (1) indentation of facing, (2) debonding between the facing and the core, (3) crushing of the core, (4) delamination between the plies of the laminated facings, (5) matrix cracking, and (6) fiber breakage in the facing. Usually, all the damage modes mentioned above can occur simultaneously.…”

Fluid based sandwich panel core structure for blast load mitigation

“…These panels have found extensive applications across diverse sectors, including aerospace, marine, transportation, and defense, owing to their advantageous characteristics [ [1] , [2] , [3] ]. Despite their widespread usage, sandwich panels are vulnerable to damage from external impacts [ [4] , [5] , [6] ]. Such damage can significantly diminish their service lifespan, load-bearing capacity, and overall functionality [ [7] , [8] , [9] ].…”