Rancang Bangun Sayap UAV Blended Winglet Menggunakan Pola Infill Grid 90° Dengan Variasi Tebal dan Panjang Sisi

Akram, Muhammad Faisal (2023) Rancang Bangun Sayap UAV Blended Winglet Menggunakan Pola Infill Grid 90° Dengan Variasi Tebal dan Panjang Sisi. Other thesis, Institut Teknologi Sepuluh Nopember.

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Abstract

Penelitian ini merupakan kelanjutan dari penelitian yang dilakukan sebelumnya mengenai optimasi sayap UAV dengan blended winglet dan rancang bangun sayap UAV dengan menggunakan teknologi pencetakan 3 dimensi. Dari penelitian sebelumnya diperoleh geometri sayap dengan winglet hasil optimasi yang kemudian digunakan pada penelitian ini. Selain optimasi sayap, telah dilakukan penelitian mengenai rancang bangun sayap UAV dengan bentuk infill tri heksagon. Pada penelitian sayap UAV dengan bentuk infill tri heksagon, dilakukan simulasi static structural dan pengujian terbang. Dari penelitian tersebut diperoleh sayap UAV belum mampu terbang karena beberapa kendala, diantaranya massa sayap yang terlalu berat, penggunaan propeller dengan diameter yang terlalu besar, dan area gerak elevator yang terlalu kecil. Dari permasalahan tersebut dibutuhkan desain struktur infill yang membuat massa sayap lebih ringan tetapi tetap kuat dan mampu diterbangkan sesuai kriteria yang ditentukan. Pada penelitian ini dilakukan pendesainan ulang struktur infill dan pengujian terbang. Adapun bentuk infill yang digunakan pada penelitian ini yaitu grid 90° dengan variasi panjang sisi dan tebal infill. Pada setiap sisi grid diberi lubang sehingga massa sayap yang dihasilkan dapat lebih ringan. Adapun secara garis besar, tahapan yang dilakukan pada penelitian ini meliputi pendesainan tiga dimensi menggunakan aplikasi Solidworks, simulasi static structural menggunakan Ansys 2021 R2, manufaktur menggunakan mesin cetak tiga dimensi, dan pengujian terbang UAV. Berdasarkan hasil uji static structural didapatkan tegangan yang terjadi pada seluruh variasi sayap masih berada di bawah tegangan izin material PLA yang telah diberi faktor keamanan 2,5 dengan nilai 24 MPa. Sayap yang dipilih yaitu sayap dengan variasi panjang sisi 55 mm dan tebal infill 0,4 mm. Variasi tersebut dipilih karena memiliki massa yang paling ringan dan memiliki tegangan maksimal yang masih di bawah tegangan izin PLA. Pemilihan sayap didasarkan pada massa yang paling ringan dikarenakan terdapat perbedaan antara evaluasi massa pada aplikasi solidworks dengan aplikasi slicer 3D printing ultimaker cura. Sebelum dicetak, desain sayap terpilih dimodifikasi menjadi beberapa bagian untuk memudahkan proses pencetakan pada mesin cetak 3D. Seluruh bagian sayap yang telah dicetak kemudian dirakit menjadi satu kesatuan sayap dan dipasangkan pada badan pesawat. Hasil dari pengujian terbang menunjukkan bahwa sayap terpilih mampu terbang, namun masih belum stabil. Ketidakstabilan tersebut bisa disebabkan oleh faktor lingkungan seperti perubahan arah dan kecepatan angin. Selain itu, sayap juga tidak dilengkapi dengan mode penerbangan stabilizer, sehingga kendali penuh terletak pada pilot.
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This research is a continuation of previous research on UAV wing optimization with blended winglets and UAV wing design using 3-dimensional printing technology. From the previous research, the wing geometry with optimized winglets was obtained which was then used in this research. In addition to wing optimization, research has been conducted on the design of UAV wings with a tri hexagon infill shape. In the research of UAV wing with tri hexagon infill shape, static structural simulation and flight testing were conducted. From this research, it was obtained that the UAV wing was not able to fly due to several obstacles, including the wing mass that was too heavy, the use of a propeller with a diameter that was too large, and the elevator motion area that was too small. From these problems, an infill structure design is needed that makes the wing mass lighter but still strong and able to fly according to the specified criteria. In this study, the redesign of the infill structure and flight testing were carried out. The form of infill used in this study is a 90 ° grid with variations in side length and infill thickness. On each side of the grid, holes are given so that the resulting wing mass can be lighter. As for the outline, the stages carried out in this study include three-dimensional design using the Solidworks application, static structural simulation using Ansys 2021 R2, manufacturing using a three-dimensional printing machine, and UAV flight testing. Based on the results of the static structural test, it is found that the stresses that occur in all wing variations are still below the PLA material permit stress that has been given a safety factor of 2.5 with a value of 24 MPa. The selected wing is the wing with a side length variation of 55 mm and an infill thickness of 0.4 mm. The variation was chosen because it has the lightest mass and has a maximum stress that is still below the PLA allowable stress. The selection of the wing is based on the lightest mass because there is a difference between the mass evaluation in the solidworks application and the ultimaker cura 3D printing slicer application. Before printing, the selected wing design was modified into several parts to facilitate the printing process on a 3D printing machine. All printed wing parts were then assembled into a single wing and attached to the fuselage. The results of the flight test showed that the selected wing was able to fly, but was still unstable. The instability can be caused by environmental factors such as changes in wind direction and speed. In addition, the wing is also not equipped with a stabilizer flight mode, so full control lies with the pilot.

Item Type:	Thesis (Other)
Uncontrolled Keywords:	Infill, Grid, PLA, Static Structural, UAV
Subjects:	T Technology > TP Chemical technology > TP1140 Polymers T Technology > TS Manufactures > TS170 New products. Product Development T Technology > TS Manufactures > TS171 Product design U Military Science > UG1242 Drone aircraft--Control systems. (unmanned vehicle)
Divisions:	Faculty of Industrial Technology and Systems Engineering (INDSYS) > Mechanical Engineering > 21201-(S1) Undergraduate Thesis
Depositing User:	Muhammad Faisal Akram
Date Deposited:	07 Aug 2023 06:09
Last Modified:	07 Aug 2023 06:09
URI:	http://repository.its.ac.id/id/eprint/103475

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