Air data system calibration for military transport aircraft modernization program

Özer, Hüseyin Erman
This thesis presents the calibration processes of the pitot-static system, which is a part of the air data system of a military transport aircraft through flight tests. Tower fly-by method is used for air data system calibration. Altitude error caused by the position of the static port on the aircraft is determined by analyzing the data collected during four sorties with different weight, flap and landing gear configurations. The same data has been used to determine the airspeed measurement error. It has been shown that both the altitude and airspeed errors are within the allowable limits specified by FAR 25. Same method is also used for trailing cone calibration that is used for high altitude test flights for RVSM certification


Aircraft motion dynamics and lateral trajectory tracking algorithm design for the enhancement of flight safety
Günhan, Cahide Yeliz; Demirbaş, Kerim; Department of Electrical and Electronics Engineering (2018)
This thesis aspires to cover the fundamentals of an aircraft control for Flight Management System (FMS). FMS, trajectory tracking and performance requirements of a flight are the focal points of the thesis. In view of this, the thesis consists of the outlined components to achieve its goal; (i) generating paths - which denotes the creation of reference paths for trajectory by complying with the avionic performance standardizations, (ii) controlling the aircraft – which propagates the control commands by usi...
Development of an autopilot for automatic landing of an unmanned aerial vehicle
Arıbal, Seçkin; Leblebicioğlu, Mehmet Kemal; Department of Electrical and Electronics Engineering (2011)
This thesis presents the design of an autopilot and guidance system for an unmanned aerial vehicle. Classical (PID) and modern control (LQT, Sliding Mode) methods for autonomous navigation and landing in adverse weather conditions are implemented. Two different guidance systems are designed in order to navigate through waypoints during normal and/or emergency flight. The nonlinear Pioneer UAV model is used in controller development and simulations. Aircraft is linearized at different trim points and total a...
Aeroelastic stability prediction using flutter flight test data
Yıldız, Erdinç Nuri; Platin, Bülent Emre; Department of Mechanical Engineering (2007)
Flutter analyses and tests are the major items in flight certification efforts required when a new air vehicle is developed or when a new external store is developed for an existing aircraft. The flight envelope of a new aircraft as well as the influence of aircraft modifications on an existing flight envelope can be safely determined only by flutter tests. In such tests, the aircraft is instrumented by accelerometers and exciters. Vibrations of the aircraft at specific dynamic pressures are measured and tr...
Improving operational performance of antennas on complex platforms by arranging their placements
Bayseferoğulları, Can; Dural Ünver, Mevlüde Gülbin; Department of Electrical and Electronics Engineering (2010)
The aim of this thesis is to improve the operational performance of the communication antennas mounted on complex platforms such as aircrafts and warships by arranging placements of these antennas. Towards this aim, primarily, in order to gain insight on the influence of geometrically simple structures composing the platform on antenna performance, a quarter wavelength monopole antenna placed at the center of a finite square ground plane is studied by using uniform Geometrical Theory of Diffraction (GTD). B...
Design and manufacturing of a high speed, jet powered target drone
Özyetiş, Ender; Alemdaroğlu, Hüseyin Nafiz; Department of Aerospace Engineering (2013)
This thesis presents the design and manufacturing of a high speed jet powered UAV which is capable of flying at M=0.5. Flight time of the UAV is 30 minutes at 1700 m above sea level. Aerodynamic and structural design of the UAV is conducted for 6g sustained and 9g instantaneous loads. Low aspect ratio blended wing-body design is decided due to low drag and high maneuverability. The Structure of the UAV consists of the composite parts such as frames and skin and mechanical parts such as landing gears which a...
Citation Formats
H. E. Özer, “Air data system calibration for military transport aircraft modernization program,” M.S. - Master of Science, Middle East Technical University, 2013.