Aeroservoelastic modeling of a missile control

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Date

2013

Author

Nalcı, Mehmet Ozan

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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

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Citation Formats

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