Electronic Theses and Dissertation

Penelitian ini dilatarbelakangi oleh kebutuhan pengembangan material sayap pesawat model yang lebih ringan, kuat, dan tahan lama dibandingkan material konvensional seperti styrofoam. Kajian pustaka menyoroti keunggulan komposit serat karbon prepreg serta efektivitas teknik vacuum bagging dan pemanasan oven dalam meningkatkan kualitas laminat. Analisis kekuatan struktur dilakukan menggunakan metode elemen hingga (Finite Element Method/FEM) untuk memodelkan respon sayap terhadap pembebanan statis. Metode penelitian meliputi pengujian sifat fisik dan mekanik melalui uji tarik sesuai standar ASTM D3039, perancangan dan pemodelan sayap menggunakan Autodesk Fusion 360, simulasi struktur menggunakan ANSYS, serta pembuatan purwarupa dengan proses laminasi prepreg, vacuum, dan curing bertahap di dalam oven. Hasil pengujian menunjukkan nilai rata-rata UTS sebesar 587,17 MPa dan modulus Young 16.765 MPa. Simulasi FEA pada ketebalan 1,5 mm menghasilkan tegangan maksimum 5,5564 MPa (pembebanan depan) dan 30,127 MPa (pembebanan ujung). Displacement masing-masing sebesar 0,14316 mm dan 17,32 mm. Purwarupa berhasil dibuat, meskipun masih ditemukan ketidakrataan pada permukaan akibat distribusi tekanan vakum yang kurang merata. Secara keseluruhan, komposit karbon prepreg terbukti layak digunakan sebagai material sayap RacingPlane Skywalker dengan performa struktural yang baik.

Kata kunci: Karbon Prepreg, Vacuum Bagging, Finite Element Method, Wings Racingplane, Komposit Pesawat.

This research was motivated by the need to develop model aircraft wing materials that are lighter, stronger, and more durable than conventional materials such as styrofoam. The literature review highlights the advantages of prepreg carbon fiber composites and the effectiveness of vacuum bagging and oven heating techniques in improving laminate quality. Structural strength analysis was performed using the finite element method (FEM) to model the wing's response to static loading. The research methods included testing physical and mechanical properties through tensile testing in accordance with the ASTM D3039 standard, wing design and modeling using Autodesk Fusion 360, structural simulation using ANSYS, and prototype production through a process of prepreg lamination, vacuuming, and gradual curing in an oven. Test results showed an average UTS value of 587.17 MPa and a Young's modulus of 16,765 MPa. FEA simulation at a thickness of 1.5 mm resulted in a maximum stress of 5.5564 MPa (front loading) and 30.127 MPa (end loading). The displacements were 0.14316 mm and 17.32 mm, respectively. The prototype was successfully produced, although unevenness was found on the surface due to uneven vacuum pressure distribution. Overall, the prepreg carbon composite proved to be suitable for use as a material for the RacingPlane Skywalker wing with good structural performance. Keywords: Carbon Prepreg, Vacuum Bagging, Finite Element Method, Wings Racingplane, Aircraft Composites.