Development of a conceptual design tool and calculation of stability and control derivatives for mini UAV systems

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Tezin Türü: Yüksek Lisans

Tezin Yürütüldüğü Kurum: Orta Doğu Teknik Üniversitesi, Fen Bilimleri Enstitüsü, Fen Bilimleri Enstitüsü, Türkiye

Tezin Onay Tarihi: 2015

Öğrenci: SENA YAZIRLI

Danışman: HÜSEYİN NAFİZ ALEMDAROĞLU

Açık Arşiv Koleksiyonu: AVESİS Açık Erişim Koleksiyonu

Özet:

The main objective of this thesis is to write a design tool that will perform the conceptual design phase of an aircraft and achieve the desired specifications of the design. For this purpose, a code is written in MATLAB so that the designer does not have to change or check parameter values when a modification on the mission altitude, cruise conditions, airfoil type, propulsion system units, weight or general geometry of the aircraft. Most of the available design tools are created for large aircraft and not for uninhabited air vehicles. Besides they are mostly focused on a single branch of the aircraft design such as airfoil design, wing design, structural design, performance analysis etc. Whereas in this thesis, it is aimed to combine all these branches of the aircraft design and come up with a conceptual design tool for mini class uninhabited air vehicles manufactured from composite materials and powered by electrical motor. The code calculates the parameters for the general geometry, lift and drag forces, pitching moment, performance characteristics, composite structure weight, stability and control derivatives, state space matrices with their eigenvalues of longitudinal and lateral dimensions. In principle, the user enters the input parameters needed and rest of the computations are done automatically. Five critical input parameters are determined by the user according to the design features. These parameters are computed by the tool and in return the user gets the optimum values for the determined objective parameters of the aircraft within the given intervals and constraints. As a results, a user-friendly conceptual design tool that generates the whole information about the aircraft from its geometry to its stability and control derivatives is devised. The thesis gives an example of the conceptual design of a mini UAV system performed using the design tool given in the thesis to verify the design tool.