Evaluation of rotorcraft system identification approaches

Kaymak, Serkan
This thesis addresses rotorcraft system identification approaches and estimating the stability and control parameters for linear system identification of a helicopter in hover. Output error and least square methods are used for the system identification. Inputs of the system identification analysis are obtained from the nonlinear helicopter model written in FLIGHTLAB commercial software environment. A linear helicopter model is used for identification. For validation, results obtained from identified helicopter model are compared with FLIGHTLAB’s nonlinear simulation results by employing different inputs which are not used in the identification procedure.


System identification and control of a fixed wing aircraft by using flight data obtained from x-plane flight simulator
Çetin, Ender; Kutay, Ali Türker; Department of Aerospace Engineering (2018)
In this thesis, a linear state-space model of an aircraft is obtained by applying numerical integration system identification method. Flight test data used in the system identification is obtained by using X-Plane flight simulation program. In X-Plane Flight Simulator, the flight tests are made by using different excitations on the control surfaces. The linear models obtained by system identification are verified by applying the inputs to the linear model and then the outputs are compared with the X-Plane f...
Comparison of rotor inflow models for flight simulation fidelity
Güner, Feyyaz; Yavrucuk, İlkay; Department of Aerospace Engineering (2016)
In real-time rotorcraft simulations, there are various dynamic inflow models to chose from. Although dynamic inflow models are well documented in literature, a comparisons of them are not commonly available. In this thesis, dynamic inflow models commonly used in flight simulators are, namely uniform inflow, extesion of uniform inflow with Payne’s coefficients, Pitt-Peters inflow and Peters-He inflow model with higher harmonics, integrated to a well-known blade element model. A theoretical background for dyn...
Performance Analysis of a Micro-scale Model Helicopter Rotor in Hover Flight
Şahin, Mustafa; Kurtuluş, Dilek Funda (2015-09-12)
This experimental study contains the design, production, test and evaluation of the test processes of a Micro-Scale Rotor Test-Rig. For the study, NACA 0012 airfoil section is selected as a rotor blade without a twist and a taper ratio. The tests cover the thrust and the torque relation with different blade pitch angles and RPM values.
A Model based approach for aircraft sensor fault detection
Serçekman, Ömür; Kutay, Ali Türker; Department of Aerospace Engineering (2018)
This thesis presents a reformative approach to a model-based fault detection and diagnosis (FDD) method that improves the capability of aircraft flight control systems and acquires low complexity and computational requirements. The main objective of the FDD techniques that are extensively applied in industrial systems is to increase the sensitivity of fault detection scheme with respect to additional noise, uncertainty or disturbances. The designed fault detection model is integrated to a civil aircraft mod...
Flight simulation and control of a helicopter
Erçin, Gülsüm Hilal; Tekinalp, Ozan; Department of Aerospace Engineering (2008)
In this thesis the development of a nonlinear simulation model of a utility helicopter and the design of its automatic flight control system is addressed. In the first part of this thesis, the nonlinear dynamic model for a full size helicopter is developed using the MATLAB/SIMULINK environment. The main rotor (composed of inflow and flapping dynamics parts), tail rotor, fuselage, vertical stabilizer, horizontal stabilizer of the helicopter are modeled in order to obtain the total forces and moments needed f...
Citation Formats
S. Kaymak, “Evaluation of rotorcraft system identification approaches,” M.S. - Master of Science, Middle East Technical University, 2013.