High by-pass turbofan engines aerothermodynamic design and optimization

Arayibi, Segun
In this thesis, a leader-follower approach is employed to make two unmanned aircrafts fly in a fixed geometrical formation. The first aircraft in the formation is designated as leader and the second is treated as the follower. The leader maintains a prescribed trajectory while the follower tracks and maintains a fixed relative distance from its leader. Since the associated kinematic equations are nonlinear, the relative guidance of the follower using two nonlinear control approaches, the Lyapunov based control algorithm and the State Dependent Riccati Equation, (SDRE) based algorithms are proposed. After the formation control problem has been solved, the follower must fly in certain attitudes for it to realize the desired flight paths needed to fly in the desired geometrical formation. This is called the attitude control problem. Simulations and tests of our proposed algorithms were carried out using a linear model of the SIG RASCAL 110 UAV for both the leader and follower UAV. Lyapunov and SDRE algorithm were used to solve the formation control problem, while linear quadratic tracking, (LQT) controllers were used on the linear models for the attitude control problems.


Real time unmanned air vehicle routing
Karabay, Nail; Köksalan, Murat; Tezcaner Öztürk, Diclehan; Department of Industrial Engineering (2018)
In this thesis, we study real-time routing of an unmanned air vehicle (UAV) in a twodimensional dynamic environment. The UAV starts from a base point, visits all targets and returns to the base point, while all targets change their locations during the mission period. We find the best route for the route planner (RP) considering two objectives; minimization of distance and minimization of radar detection threat. We develop a real-time algorithm to find the UAV’s most preferred route for a RP who has an unde...
Vision-aided landing for fixed wing unmanned aerial vehicle
Esin, Engin; Kutay, Ali Türker; Department of Aerospace Engineering (2016)
The aim of this thesis is to design an autoland system for fixed wing unmanned aerial vehicle (UAV) to make auto landing by using position information calculated by image processing algorithms. With this ability, even if GPS is not available to be used, UAV still could make a safe automatic landing. Landing autopilot is aimed to keep UAV on a straight line with a constant flight path angle. Therefore, landing autopilot and computer vision methods are studied within the scope of this thesis. Also, to test de...
Modeling and control of quadrotor formations carrying a slung load
Ariyibi, Segu; Tekinalp, Ozan; Department of Aerospace Engineering (2019)
In this thesis, an algorithm for the autonomous formation flight of quadrotors carrying a slung load is developed. Full nonlinear models for a single quadrotor carrying a slung load as well as two and three quadrotors carrying a slung load problems are addressed. For the two and three quadrotor slung load systems, a leader-follower approach is employed to make the quadrotors fly in a fixed geometrical formation. The overall control algorithm employs a loop structure with a Lyapunov based formation guidance ...
Landing autopilot design for an unmanned aerial vehicle /
Ak, Ayşe İlden; Leblebicioğlu, Mehmet Kemal; Department of Electrical and Electronics Engineering (2014)
In this thesis, studies for the development of a landing autopilot for the UAV (Unmanned Aerial Vehicle), Pioneer RQ2 are presented. Firstly, 6 DOF (degree of freedom) nonlinear model of Pioneer is implemented in Matlab-Simulink based on FDC (Flight Dynamics and Control) Toolbox. Then, in accordance with steady-state wings level flight condition, trim points are found for different airspeed values, constant height and zero flight path angle. The nonlinear model of Pioneer is linearized at these trim points ...
System identification using flight test data
Şimşek, Orkun; Tekinalp, Ozan; Department of Aerospace Engineering (2014)
In this study, a linear model of an unmanned aerial vehicle (UAV) is developed by using frequency domain system identification methods. The data used in the identification methods are obtained by performing flight tests. To obtain appropriate flight test data for identification process, flight test maneuvers are designed. These flight test data are used in two main frequency domain system identification methods, namely, transfer function modeling and state space modeling. The linear models obtained by using...
Citation Formats
S. Arayibi, “High by-pass turbofan engines aerothermodynamic design and optimization,” M.S. - Master of Science, Middle East Technical University, 2014.