Aerodynamic parameter estimation of a missile in closed loop control and validation with flight data

Download
2012
Aydın, Güneş
Aerodynamic parameter estimation from closed loop data has been developed as another research area since control and stability augmentation systems have been mandatory for aircrafts. This thesis focuses on aerodynamic parameter estimation of an air to ground missile from closed loop data using separate surface excitations. A design procedure is proposed for designing separate surface excitations. The effect of excitations signals to the system is also analyzed by examining autopilot disturbance rejection performance. Aerodynamic parameters are estimated using two different estimation techniques which are ordinary least squares and complex linear regression. The results are compared with each other and with the aerodynamic database. An application of the studied techniques to a real system is also given to validate that they are directly applicable to real life.

Suggestions

Vortex generator design for subsonic inlets
Nasuhbeyoğlu, Batuhan; Albayrak, Kahraman; Department of Mechanical Engineering (2014)
In this thesis, numerical investigation of the benefits of vortex generators control on the performance of S-shaped inlets has been performed. This study is divided into two main parts. In the first part, a diffusive S-shaped inlet is examined and the numerical analyses results are compared with the experimental results. Three-dimensional Navier-Stokes equations are solved and three different turbulence models which are Realizable k-ε, Standard k-ω, and Spalart-Allmaras methods are used. Distortion coeffici...
Flight test maneuver design and aerodynamic parameter estimation for single use autonomous air vehicles
Vefa Yavuzturk, N.; Topbas, Eren; Yazıcıoğlu, Yiğit (null; 2017-01-01)
In this paper, a maneuver design and aerodynamic parameter estimation procedure is carried out for single use autonomous gliding air vehicles where allowable flight testing time is limited. At first, using the priori aerodynamics of a gliding vehicle, an aerodynamic model has been built and six degree of freedom simulation tool is generated. This priori aerodynamic knowledge is used to design a multi-sine input to excite the system at predetermined flight conditions during flight test. Afterwards, using the...
Experimental investigation of the effects of tip-injection on the aerodynamic loads and wake characteristics of a model horizontal axis wind turbine rotor
Abdulrahim, Anas; Uzol, Oğuz; Department of Aerospace Engineering (2014)
In this study, tip injection is implemented on a model Horizontal Axis Wind Turbine (HAWT) rotor to investigate the power and thrust coefficient variations as well as the wake characteristics. The model wind turbine has a 0.95 m diameter 3-bladed rotor with non-linearly twisted and tapered blades that has NREL S826 profile. The nacelle, hub and the blades are specifically designed to allow pressurized air to pass through and get injected from the tips while the rotor is rotating. The experiments are perform...
Parallel computation of flows around flapping airfoils in biplane configuration
Tuncer, İsmail Hakkı; Kaya, Muhammed Çağrı (2002-05-22)
Unsteady, laminar flows over flapping airfoils in biplane configuration are computed on overset grids. The overset grid solutions are obtained in parallel in a cluster environment. It is shown that airfoils in biplane configuration and oscillating in pitch and plunge with a proper phase shift between them enhance the thrust production significantly.
Aerodynamic modeling and parameter estimation of a quadrotor helicopter
Kaya, Derya; Kutay, Ali Türker (2014-01-01)
This study focuses on aerodynamic modeling of a quadrotor helicopter and the estimation of the model parameters in wind tunnel tests for hover, vertical climb, and forward flight conditions. The motion of a quadrotor is mainly affected by the aerodynamic forces and moments generated by rotors. Accurate calculation of rotor loads is essential for high fidelity simulation of a quadrotor. Momentum and blade element theories are used to obtain expressions for rotor forces and moments for a traveling vehicle. Th...
Citation Formats
G. Aydın, “Aerodynamic parameter estimation of a missile in closed loop control and validation with flight data,” M.S. - Master of Science, Middle East Technical University, 2012.