Vol 2, No 3 ( Published)

DOI: http://dx.doi.org/10.18063/msacm.v2i3

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Table of Contents

Original Research Articles

by Liping Liu 1, Yucan Wang 1, Jing Tian 1, Ruifeng Wang 1, Jianxin Xu 1
268 Views, 79 PDF Downloads
Composite laminates are widely used in the large civil aircrafts because of their excellent mechanical properties. The maintenance and repair of composite laminates become essential. In this paper, a new adhesive-rivet hybrid repair of composite laminate fuselage skin is presented. For the circular hole damage with the diameter of 90mm and 50mm, the finite element simulation models of adhesive repair and adhesive-rivet hybrid repair were built respectively. Uniform pressure load was applied on these finite element models. The mechanical properties of laminate motherboard, patch and adhesive film for these four models were analyzed. The effects of adhesive repair, adhesive-rivet hybrid repair on mechanical behaviors of repair areas of composite laminate fuselage skins with different damage size were studied. By analyzing the mechanical behaviors of these two repair methods, a suitable repair method can be obtained.

Original Research Articles

by Jie Zhao 1,2, Wenjun Wang 1,2, Ruijia Wang 1,2, Jianlei Cui 1,2
438 Views, 89 PDF Downloads
A 3.5 mm thick SiCf/SiC material was drilled in air environment using a femtosecond laser filament effect. The surface morphology of deep micropores was observed by scanning electron microscopy and the depth and profile of the pores were observed using μm-CT. The variation of entrance diameter, exit diameter and depth variation with laser focus position and processing time was further analyzed. The results showed that as the processing time of femtosecond laser increases, the ablation threshold of the material reached saturation. The exit and entrance diameter also stopped increasing and the aperture tend to saturate. The focus entered the interior of the material, allowing the location of the peak power near the surface of the material. So the entrance aperture was of good quality and the exit aperture was round.

Original Research Articles

by Prashant Rawat 1, K. K. Singh 2, B. N. Tripathi 1
258 Views, 90 PDF Downloads
This paper examines the mechanical performance of eight-layered GFRP laminate embedded with short carbon fibers (SCF). Eight layered GFRP samples are prepared using press molding machine at 40 KN pressure. Notched samples (1 mm deep) at specific position from the center are tested, the doping of SCF is done to evaluate the improvement in mechanical properties using reinforcement at three different proportions 0, 1, 2 and 5 wt.%. The GFRP samples are prepared as per ASTM D2344 and ASTM D7264 for short beam strength (SBS) and flexural and respectively. Samples are tested using Hounsfield HK-50 universal testing machine (UTM) with 50KN capacity at room atmospheric conditions. Results of the experimental analysis justified that the improvement in mechanical properties with increase in doping percentage of SCF while at highest doping value i.e. 5 wt.% mechanical properties reduced.