Reliability analysis of tactical unmanned aerial vehicle (UAV)

Download
2017
Koç, Yılmaz
To design cost effective and reliable products are considered to be important to be competitive in the Aerospace Industry. Reliability is therefore, taken as an integral part of the design process. Reliability, which is a kind of design parameter that affects cost and system safety, shall be taken into account in early phases of design process due to difficulties facing during changes in design at the later phases. Reliability of Tactical UAVs can be evaluated by reliability testing but these tests are very expensive and difficult. Because of the difficulties in reliability testing, in early design phases reliability can be evaluated by using reliability methods. In the scope of this thesis work, simulation study is performed to make reliability prediction for METU Tactical UAV. Two different approaches are used to calculate reliability characteristics for systems of METU Tactical UAV. The approaches applied during simulation study are; firstly, items failure characteristics (i.e. failure rate) are taken as a constant and thus exponential distribution is used as probability distribution model. Second approach was that simulated time to failure data having Weibull distribution characteristic is derived and it is determined to show how predicted reliability changes if it is assumed to be exponentially distributed. Within the context of this simulation study, graphical methods i.e. Quantile-Quantile plotting and probability-probability plotting were conducted to find the best distribution model. Three-parameter Weibull distribution is taken as primary model to assess simulated data and unknown parameters of Weibull distribution for which Goodness - of - Fit Tests have been applied is estimated by using Maximum Likelihood and Least Square Estimation. This simulation study is conducted to emphasis the effect of assumption on distribution model, which represent the simulated data.

Suggestions

Reliability Analysis of Tactical Unmanned Aerial Vehicle (UAV)
Sürücü, Barış; Alemdaroğlu, Hüseyin Nafiz (2017-09-20)
To be competitive in the market, it is very important to design cost effective and reliable products. For this purpose, it is necessary to consider reliability as an integral part of the design procedure. Therefore, reliability which is a design parameter that affects cost and safety of a system should be taken into consideration in early phases since it is very difficult to change design at the later phases. Due to these causes the importance of reliability in manufacturing fields, especially in aviat...
Aerodynamic and structural design and analysis of an electric powered mini UAV
Demircan, Alpay; Kayran, Altan; Department of Aerospace Engineering (2016)
The aim of this study is to describe the aerodynamic and structural design of an electric powered portable Mini UAV. Conceptual design, structural design and analysis of the wing and detail design phases of the UAV are presented in the study. Fixed wing mini UAV configuration with fixed – pitch propeller has been chosen for the design. In order to provide multi-mission capability, payload of the UAV is designed as a replaceable mission compartment. System requirements and mission profiles of the airplane ar...
Design of a medium range tactical UAV and improvement of its performance by using winglets
Turanoğuz, Eren; Alemdaroğlu, Hüseyin Nafiz; Department of Aerospace Engineering (2014)
The study encompasses the design, performance analysis and aerodynamic improvement of the designed medium range tactical unmanned aerial vehicle. Main requirements are set as following; cruising altitute above 3500m, endurance of approximately 10-12 hours, range of 150 km and payload of 60 kg. The conventional design phase is based on the employment of historical equations and experiences. Nowadays, employement of well known equations and experiences during the desing process are not enough to reveal a comp...
Conceptual design of a stealth unmanned combat aerial vehicle with multidisciplinary design optimization
Çakın, Uğur; Alemdaroğlu, Hüseyin Nafiz; Department of Aerospace Engineering (2018)
The present study aims to develop a methodology for multi-disciplinary design optimization (MDO) of an unmanned combat aerial vehicle. At the current stage of optimization study, three disciplines are considered, which are aerodynamics, structural weight and radar cross section (RCS) signature. As objective functions, maximum range and minimum RCS signature are employed. To generate pareto-optimal solutions, multi-objective particle swarm optimization (MOPSO) function of MATLAB® is performed. To get aerodyn...
Development of a conceptual design tool and calculation of stability and control derivatives for mini UAV systems
Yazırlı, Sena; Alemdaroğlu, Hüseyin Nafiz; Department of Aerospace Engineering (2015)
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...
Citation Formats
Y. Koç, “Reliability analysis of tactical unmanned aerial vehicle (UAV),” M.S. - Master of Science, Middle East Technical University, 2017.