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

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Date

2012

Author

Aydın, Güneş

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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.

Subject Keywords

Aerodynamics., Fluid dynamics., Viscous flow., Vortex-motion.

URI

http://etd.lib.metu.edu.tr/upload/12615100/index.pdf
https://hdl.handle.net/11511/21959

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Graduate School of Natural and Applied Sciences, Thesis

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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.