Abstract

In this paper, fiber waviness, as one of the most frequently occurring defects in fiber reinforced composites, is numerically investigated with regard to the formation of residual stresses in fiber metal laminates. Furthermore, the prediction of the residual stress state in the thickness direction by means of the simulated hole drilling method is studied. To this regard, a global-local finite element analysis based on the submodel technique is presented. The submodel technique essentially consists of two governing steps: In the first step, a global model is first utilized to calculate and analyze the residual stress distribution and deformation in the intrinsically joined hybrid structure. Effective cure-dependent thermo–elastic properties predicted by a numerical homogenization procedure were used to simulate the curing-process and analyze the residual stresses state. However, the dimension of the intrinsically manufactured hybrid plate is large compared to the diameter of the drilled hole (2 mm), so that a local model is necessary, which provides only a geometric partial portion of the global model. The local model takes the global stress state into account and is subsequently used to simulate the incremental hole drilling method with a refined mesh discretization. The production-related fiber waviness is modeled by an element-wise orientation approximating a sinus function. In order to validate the global-local modeling approach, a comparison between numerical results and experimental data from literature is presented. The comparison between global residual stress state (global model) and the simulated hole drilling method (local model) is used to assess the applicability and reliability of the hole drilling method in case of fiber waviness. It is found that an in-plane fiber waviness leads to a rather low variance of residual stresses over thickness. In case of an out-of-plane fiber waviness, oscillating residual stress fields occur over the entire thickness along the fiber direction. Moreover, the current limits of the incremental hole drilling method could be pointed out by the presented investigations. It is seen that the simulated results of the incremental hole drilling method are sensitive to waviness, even if the amplitude-wavelength-ratio is small. Without further adjustment of the calibration coefficients the oscillating stress and strain fields lead, in particular fiber waviness in thickness direction, to unreliable predictions. For the experimental application it can be concluded that the specimens have to be carefully examined with regard to fiber waviness.

Highlights

  • Today an automotive body in white (BIW) is inspired by a multi material design

  • The influence of the amplitude and wavelength of the fiber waviness is small on the carbon fiber reinforced plastics (CFRP) side, while the deviation at the interface on the metal side is approximately 17 MPa, whereas on the free outer surface of the metal the deviation is reduced to approximately 7 MPa

  • It is of high importance to investigate the influence of the fiber waviness on the overall residual stress state and the applicability of the incremental hole drilling method

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Summary

Introduction

Today an automotive body in white (BIW) is inspired by a multi material design. In addition to classical lightweight materials like aluminum and magnesium alloys, advanced high strength steels (AHSS) are increasingly used due to high strength, good formability and enhanced crash performance. Carbon fiber reinforced plastics (CFRP) offers superior lightweight characteristics and high energy absorption [1]. CFRP have not achieved an acceptance like metals, which can be related to their comparably high production cost [2]. Hybrid materials allow to combine metals and CFRP in a manner to offset the drawbacks of every single material and reach an optimum of mechanical properties and costs. The comparably expensive lightweight material is only partially used for local reinforcement of mechanically highly stressed regions, such as b-pillars or roof beams [3]. In addition to the application of hybrid materials in the body of white concepts, fiber metal laminates (FML) are extensively used in aircraft structures, due to their excellent damage tolerance and high weight saving potential compared to solitaire materials [4]

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