Aeroservoelastic modeling of a missile control

Download

index.pdf

Date

2013

Author

Nalcı, Mehmet Ozan

Metadata

Show full item record

Item Usage Stats

295
views

141
downloads

In this thesis, aeroservoelastic modeling of a typical Missile Control Fin was performed. MSC®PATRAN, MSC®NASTRAN, MSC®FlightLoads and Dynamics, MATLAB® and MATLAB®Simulink were used for technical computing, modeling and simulation throughout the study. Linear models of the control fin structure, aerodynamics and servo-actuator system were developed, so as to be able to analyze the aeroservoelastic system in frequency and time domains. The flutter characteristics of the missile control fin for different flight conditions were obtained and presented. Time history of the control fin elastic deflection under unsteady aerodynamic loads, for various actuator commands is simulated. An aeroservoelastic model development strategy is presented, such that the interaction between servo-actuator system dynamics and aeroelastic properties of the control fin could be revealed.

Subject Keywords

Aeroelasticity., Aeroservoelasticity., Flutter (Aerodynamics)., Guided missiles

URI

http://etd.lib.metu.edu.tr/upload/12615904/index.pdf
https://hdl.handle.net/11511/22538

Collections

Graduate School of Natural and Applied Sciences, Thesis

Suggestions

OpenMETU
Core

Fuzzy logic guidance system design for guided missiles Vural, A. Özgür; Özgören, Mustafa Kemal; Merttopçuoğlu, Osman; Department of Mechanical Engineering (2003) This thesis involves modeling, guidance, control, and flight simulations of a canard controlled guided missile. The autopilot is designed by a pole placement technique. Designed autopilot is used with the guidance systems considered in the thesis. Five different guidance methods are applied in the thesis, one of which is the famous proportional navigation guidance. The other four guidance methods are different fuzzy logic guidance systems designed considering different types of guidance inputs. Simulations ...
Aeroservoelastic Modelling and Analysis of a Missile Control Surface with a Nonlinear Electromechanical Actuator Mehmet Ozan, Nalcı; Kayran, Altan (null; 2014-06-16) In this study, aeroservoelastic modeling and analysis of a missile control surface which is operated and controlled by a power limited, nonlinear electromechanical actuator is performed. Linear models of the control fin structure and aerodynamics together with the nonlinear servo-actuation system are built and integrated. The resulting aeroservoelastic system is analyzed both in time and frequency domain. Structural model of the control fin is based on the finite element model of the fin. Aerodynamic model ...
Three dimensional aerodynamic analysis of missiles by a panel method Başoğlu, Osman; Özyörük, Yusuf; Department of Aeronautical Engineering (2002) Panel methods are extensively used in aerodynamic analysis of missiles in early stages of their development. An existing TUBİTAK-SAGE panel code is modified and improved for routine and more efficient calculation of the aerodynamic coefficients of various missile configurations at subsonic and supersonic flight conditions. Particularly, the poor convergence, user unfriendliness and poor output characters of this code have been improved by modifying and adding new routines to it. Now the code with an incorpo...
Missile autopilot design by projective control theory Doruk, Reşat Özgür; Kocaoğlan, Erol; Department of Electrical and Electronics Engineering (2003) In this thesis, autopilots are developed for missiles with moderate dynamics and stationary targets. The aim is to use the designs in real applications. Since the real missile model is nonlinear, a linearization process is required to get use of systematic linear controller design techniques. In the scope of this thesis, the linear quadratic full state feedback approach is applied for developing missile autopilots. However, the limitations of measurement systems on the missiles restrict the availability of ...
Aerodynamic parameter estimation of a missile Aksu, Arda; Kutay, Ali Türker; Department of Aerospace Engineering (2013) Aerodynamic characteristics of missiles depend strongly on wind angles, that is, angle of attack and sideslip angle. However it is impractical to measure these angles during missile testing. Therefore, without direct information of the wind angles, it becomes a difficult problem to be able to accurately estimate the missile aerodynamic parameters from flight tests. This thesis addresses this problem and suggests an approach to estimate missile aerodynamic parameters successfully without wind angles measurem...

Citation Formats

M. O. Nalcı, “Aeroservoelastic modeling of a missile control,” M.S. - Master of Science, Middle East Technical University, 2013.