PROGRESSIVE DAMAGE ANALYSIS ON OPEN HOLE LAMINATED CFRP COMPOSITE PLATE WITH VARIOUS CONFIGURATIONS DUE TO COMPRESSION LOAD

• Main Author: Solihat, Aat
• Format: Theses
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/35020
• Institution: Institut Teknologi Bandung

The hole in the joint or composite panel has potential to reduce the strength of the material [9], the hole in this panel becomes a reference to the progressive failure model of each ply in composite laminate, when the part experiences tensile loads, compression or shear due to moment and torque forces. This paper focuses on the effect of a compressive load on the strength and progressive failure of the material structure of the panels around the hole. Observations were made on the pattern, based on the numerical method, then the results were compared with the specimen test results. Specimen testing starts from the composite panel manufacturing stage to form a specimen, then performs a compression test for the four specimen configurations of each of the five items based on ASTM D6484 standard. The test results showed that the UD-8126 specimen failed at a compression load of 4119.43 kgf, UD-8128 at 5509.26 kgf, Fabric-8224 at 3724.1 kgf and Fabric-8226 at 6093.42 kgf. Numerical modeling analysis was carried out as a comparison of the test results. The aim of the analysis was to predict the progressive damage of open hole laminate composite plates using three failure criteria, namely Tsai-Hill, Hoffman and Puck. The results of the four specimen simulations with three failure criteria show different results. Judging from the percentage of the error value of the numerical results of the symmetric balance composite material (8128, 8224, 8226) against the test results as follows, Tsai-Hill [11.6-16.08]%, Hoffman (4.2-15.9)% and Puck (34.8-48.4)%. From these results, Hoffman's failure criteria are