ANALISIS STATIS DAN BEBAN AERODINAMIKA STRUKTUR FLAPPING WING MICRO AIR VEHICLE (FW-MAV)

*Miftahul Anwar  -  Department of Mechanical Engineering, Universitas Diponegoro, Jl. Prof. Sudarto, SH, Tembalang, Semarang, Indonesia 50275, Indonesia
Ismoyo Haryanto  -  Department of Mechanical Engineering, Universitas Diponegoro, Jl. Prof. Sudarto, SH, Tembalang, Semarang, Indonesia 50275, Indonesia
Achmad Widodo  -  Department of Mechanical Engineering, Universitas Diponegoro, Jl. Prof. Sudarto, SH, Tembalang, Semarang, Indonesia 50275, Indonesia

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Abstract
Dalam dunia penerbangan di zaman modern ini, kendaraan udara berdimensi kecil sudah banyak dikembangkan salah satunya yaitu Flapping Wing Micro Air Vehicle (FW-MAV). Jenis kendaraan ini memiliki sayap yang mengepak saat terbang, sehingga analisis struktur dan aerodinamika sangat penting untuk dianalisis lebih lanjut untuk mendapatkan rancangan sayap yang lebih baik. Material dari sayap pada penelitian ini yaitu graphite-epoxy rods dan kapton film. Analisis dilakukan dengan menggunakan software Ansys Mechanical Worbench dan Ansys Fluent. Analisis struktural pada penelitian ini menggunakan pembebanan statik dimana beban didapat dari analisis Computational Fluid Dynamics (CFD) yaitu sebesar 0.07 Pa. Nilai total deformasi yang didapat yaitu maksimum di ujung sayap sebesar 36,165 mm dan minimum sebesar 0 mm disekitar rod penyangga sayap. Analisis aerodinamika dilakukan dengan variasi sudut serang 0⁰ sampai 6⁰, dimana didapat hasil berupa empat parameter Coefficient of Drag (), Coefficient of Lift (), drag dan lift. Hasil dari analisis aerodinamika menunjukkan bahwa semakin besar sudut serang yang diaplikasikan maka nilai dari , , drag dan lift juga akan semakin meningkat.
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Keywords: drag; flapping wing; lift; statik
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