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Ditemukan: 3 dokumenANALISIS PEMBEBANAN STATIS DAN SPEKTRUM BEBAN PADA STRUKTUR PROPELLER KOMPOSIT PESAWAT TURBOPROP
Baling-baling merupakan komponen krusial pada pesawat turboprop yang menuntut integritas struktural tinggi terhadap beban aerodinamika dan momentum rotasi guna menjamin performa serta keselamatan operasional. Penelitian ini berfokus pada perancangan dan analisis kekuatan propeller dengan mengintegrasikan metode General Momentum Theory (GMT) dan Blade Element Theory (BET), atau yang dikenal sebagai Blade Element Momentum Theory (BEMT). Melalui prosedur desain berbasis metode Larrabee, distribusi beban aerodinamika dihitung secara presisi pada setiap elemen bilah untuk menentukan gaya dorong dan daya yang dibutuhkan sesuai kondisi terbang target. Spektrum beban lokal yang dihasilkan kemudian digunakan sebagai parameter batasan dalam perancangan struktur manufaktur berbasis material berlapis dan penguatan spar. Pendekatan ini memastikan bahwa geometri baling-baling tidak hanya optimal secara aerodinamis, tetapi juga memiliki ketahanan struktural yang mumpuni dalam menghadapi beban dinamis selama operasional.
SIMULATION OF FIBER BRIDGING IN UNIDIRECTIONAL COMPOSITES USING THE FINITE ELEMENT METHOD IN A DOUBLE CANTILEVER BEAM TEST
Delamination is a critical failure mode in fiber-reinforced polymer composites, often causing severe structural issues. This study develops and validates a finite element model (FEM) to simulate how transverse fiber bridging affects fracture toughness in unidirectional carbon fiber reinforced polymer (CFRP) composites during Double Cantilever Beam (DCB) tests. The model uses shell elements to represent the bending behavior and rotational effects of bridging fibers, with cohesive interactions assigned through a Weibull distribution to capture variability in interfacial properties. Validation was conducted using experimental data from Ping Hu et al. The simulation results without fiber bridging aligned well with analytical predictions, while the inclusion of fiber bridging reproduced experimental trends such as increased fracture toughness and load–displacement curve fluctuations. Parametric analysis revealed that greater specimen width and smaller bridging dimensions both enhanced toughness. Overall, the validated FEM provides insights for optimizing fiber bridging to improve the damage resistance of composites.
FINITE ELEMENT ANALYSIS ON LOW VELOCITY IMPACT AND COMPRESSION AFTER IMPACT OF COMPOSITE LAMINATE
The usage of composite material have been increasing the last decades, especially in industries such as aerospace and automotive. However, one of the concerns regarding the usage of composite is its susceptibility to damage due to low velocity impact (LVI). LVI can cause a barely visible impact damage (BVID) which can compromise the compression strength significantly. In this reseach, finite element method (FEM) models based on Kirchoff’s Plate Theory, Hashin-Rottem damage modelling, and Benzggagh-Kenane fracture criterion are proposed to simulate the low velocity impact and compression after impact (CAI) on composite laminate. The models are modelled and validated with existing experiment data. The FEM model is used to find the relationship between the impact energy and laminate orientations on the CAI strength. The developed model could predict the composite behaviour considerably well. The LVI impact energy is found to have an inverse power law relationship with the CAI strength. The laminates with more 0 degree plies tends to have higher compression strength while laminate with ±45 tends to have better damage resistance.