Susanto, Thomas Prayoga (2026) Optimasi Struktur Auxetic untuk Aplikasi Spanwise Morphing Wing pada UAV Multi-Misi melalui Pendekatan Finite Element Analysis (FEA) dan Validasi Eksperimental. Other thesis, Institut Teknologi Sepuluh Nopember.
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Abstract
Perkembangan Unmanned Aerial Vehicle (UAV) multi-misi memerlukan konfigurasi sayap yang dapat beradaptasi terhadap kebutuhan jelajah dan manuver. Penelitian ini mengembangkan struktur auxetic Hybrid Re-Entrant Star sebagai adaptive compliant core untuk spanwise morphing wing. Enam parameter geometri dioptimasi menggunakan Finite Element Analysis (FEA) dan Adaptive Multiple-Objective Optimization pada ANSYS dengan tiga respons yang dipertimbangkan bersamaan, yaitu deformasi spanwise, tegangan ekuivalen, dan gaya aktuasi. Material PETG hasil fused deposition modeling (FDM) dikarakterisasi melalui tiga spesimen uji tarik. Rata-rata Young's modulus, yield strength metode offset 0,2%, ultimate tensile strength, dan tangent modulus yang diperoleh berturut-turut sebesar 1703,21 MPa, 34,90 MPa, 47,13 MPa, dan 648,12 MPa. Dibandingkan desain baseline, hasil optimasi meningkatkan displacement tarik dari sekitar 5,8 mm menjadi 52 mm dan displacement tekan dari sekitar 5,7 mm menjadi 40 mm. Rentang morphing total mencapai sekitar 92 mm atau 42,99% terhadap span awal 214 mm. Gaya aktuasi tarik turun dari 1117,2 N menjadi 26,8 N, sedangkan gaya tekan turun dari 1096,1 N menjadi 52,8 N. Tegangan maksimum baseline sebesar 48,31 MPa menurun menjadi 24,2 MPa, sehingga desain optimasi berada di bawah yield strength PETG. Pada validasi tekan, gaya akhir simulasi sebesar 52,8 N dibandingkan dengan 59 N pada eksperimen, dengan error titik akhir 10,4%. Pada validasi tarik, gaya akhir simulasi dan eksperimen masing-masing sekitar 26,8 N dan 25 N, dengan perbedaan sekitar 6,73%. Kesamaan tren global menunjukkan bahwa model memadai untuk screening desain, tetapi belum dapat dianggap sebagai prediktor kuantitatif final karena material FDM dimodelkan homogen-isotropik dan pengulangan validasi struktur masih terbatas. Namun, penurunan kekakuan aksial pada struktur hasil optimas menyebabkan trade-off terhadap penurunan kakuan lentur dari struktur, sehingga perlu di integrasikan dengan mekanisme atau sistem pengaku tambahan, seperti kulit dan linear actuator. Melalui integrasi sistem tambahan tersebut dilakukan nalisis fluid-structure satu arah pada kondisi steady-state untuk menguji kemampuan struktur dalam pembebanan aerodynamis, hasil menunjukkan deformasi maksimum 0,0244 mm dan tegangan maksimum 0,296 MPa sehingga mendukung kelayakan awal konsep sebagai inti adaptif, dengan skin dan sistem aktuasi berfungsi sebagai jalur pengaku terhadap pembebanan luar bidang.
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The development of multi-mission Unmanned Aerial Vehicles (UAVs) requires wing configurations that can adapt to different endurance and maneuverability demands. This study develops a Hybrid Re-Entrant Star auxetic structure as an adaptive compliant core for a spanwise morphing wing. Six geometric parameters were optimized using Finite Element Analysis (FEA) and Adaptive Multiple-Objective Optimization in ANSYS, with three responses considered simultaneously: spanwise deformation, equivalent stress, and actuation force. The mechanical properties of fused deposition modeling (FDM)-fabricated PETG were characterized using three tensile-test specimens. The average Young’s modulus, 0.2% offset yield strength, ultimate tensile strength, and tangent modulus were 1703.21 MPa, 34.90 MPa, 47.13 MPa, and 648.12 MPa, respectively. Compared with the baseline design, the optimized design increased the tensile displacement from approximately 5.8 mm to 52 mm and the compressive displacement from approximately 5.7 mm to 40 mm. The total morphing range reached approximately 92 mm, corresponding to 42.99% of the initial span of 214 mm. The tensile actuation force decreased from 1117.2 N to 26.8 N, while the compressive actuation force decreased from 1096.1 N to 52.8 N. The maximum stress of the baseline design decreased from 48.31 MPa to 24.2 MPa, placing the optimized design below the PETG yield strength. In the compression validation, the final simulated force was 52.8 N, compared with 59 N in the experiment, resulting in an endpoint error of 10.4%. In the tensile validation, the final simulated and experimental forces were approximately 26.8 N and 25 N, respectively, corresponding to a difference of approximately 6.73%. The similarity in the global response trends indicates that the model is adequate for design screening. However, it cannot yet be considered a final quantitative predictor because the FDM material was modeled as homogeneous and isotropic, and the number of structural validation repetitions was still limited. Nevertheless, the reduction in axial stiffness of the optimized structure produced a trade-off in the form of reduced bending stiffness. Therefore, the structure must be integrated with additional stiffening mechanisms or systems, such as a wing skin and a linear actuator. Following the integration of these additional systems, a one-way fluid–structure interaction analysis under steady-state conditions was conducted to evaluate the structural response under aerodynamic loading. The results showed a maximum deformation of 0.0244 mm and a maximum equivalent stress of 0.296 MPa. These findings support the initial feasibility of the concept as an adaptive core, with the skin and actuation system serving as additional load paths and stiffening elements against out-of-plane loading.
| Item Type: | Thesis (Other) |
|---|---|
| Uncontrolled Keywords: | struktur auxetic, spanwise morphing wing, PETG, finite element analysis, optimasi geometri, validasi eksperimen, one-way fluid-structure interaction, auxetic structure, spanwise morphing wing, PETG, finite element analysis, geometric optimization, experimental validation, one-way fluid-structure interaction |
| Subjects: | T Technology > TA Engineering (General). Civil engineering (General) > TA347 Finite Element Method T Technology > TJ Mechanical engineering and machinery U Military Science > U Military Science (General) > UG Military Engineering > UG1242.D7 Unmanned aerial vehicles. Drone aircraft |
| Divisions: | Faculty of Industrial Technology and Systems Engineering (INDSYS) > Mechanical Engineering > 21201-(S1) Undergraduate Thesis |
| Depositing User: | Thomas Prayoga Susanto |
| Date Deposited: | 01 Aug 2026 07:12 |
| Last Modified: | 01 Aug 2026 07:14 |
| URI: | http://repository.its.ac.id/id/eprint/141592 |
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