CD Skripsi

Perancangan Pesawat Terbang Tanpa Awak Vertical Take Off – Landing Tipe Tail-Sitter (Design Of Unmanned Aerial Vehicle Vertical Take Off – Landing Tail-Sitter Type)

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ABSTRACT
Fixed wing unmanned aircraft have several weaknesses including requiring a large area for take off and landing, requiring a launcher as an additional tool for take off and having a high crash risk during landing. because the vehicle does not use landing gear. So that the above weaknesses can be corrected, it is necessary to conduct research related to the development of a tail-sitter type of Vertical Take Off - Landing (VTOL). This study aims to produce a tail-sitter vehicle design, determine the strength of the structure and determine the estimated battery capacity for a 25-minute flight from the tail-sitter vehicle. The research starts from determining the design requirement objective and calculating the wing dimensions. Next, calculate the aerodynamic characteristics of the airfoil and fuselage. Calculation of airfoil aerodynamic characteristics and fuselage design using Ansys software. Next, make a complete design of the tail-sitter vehicle and perform structural static calculations to determine the strength of the tail-sitter structure using the Ansys software. Finally calculate the estimated battery capacity for the pilot for 25 minutes. The tail-sitter wing has been successfully designed with a lift coefficient of 0.83185 and a lift to drag ratio of 84,16466. The tail-sitter fuselage has been successfully designed with an airfoil profile that has a drag coefficient value of 0.01984. From the simulation of the strength of the tail-sitter structure in the take-off phase, the maximum deflection value occurs at the wingtip of 3.7237 mm, the maximum stress occurs at the joint between the spar and the fuselage of 17.391 MPa and the minimum safety factor value is 3.6281. From the simulation of the strength of the tail-sitter structure in the cruise phase, the maximum deflection value occurs at the wingtip of 6.0993 mm, the maximum stress occurs at the joint between the spar and the fuselage of 21.984 MPa and the minimum safety factor value is 4.5606. From the calculation of the estimated battery capacity, the tail-sitter can fly for 25 minutes with a battery capacity of 11,610 mAh.
Keywords: Fixed wing, VTOL, Tail-sitter, Fuselage, Sayap, Ansys.

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Ketersediaan

Informasi Detail

Judul Seri

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No. Panggil

1707113961

Penerbit

Pekanbaru : Universitas Riau – Fakultas Teknik – Teknik Mesin., 2022

Deskripsi Fisik

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Bahasa

Indonesia

ISBN/ISSN

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Klasifikasi

1707113961

Tipe Isi

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Tipe Media

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Tipe Pembawa

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Edisi

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Subjek

TEKNIK MESIN

Info Detail Spesifik

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Pernyataan Tanggungjawab

daus

Versi lain/terkait

Lampiran Berkas

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