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Development of Aerodynamic and Propulsion Models Using the Iterative Equation Error Method
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Date
2024-01-01
Author
Millidere, Murat
Akgül, Ferhat
Leblebicioğlu, Mehmet Kemal
Whidborne, James F.
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This work is licensed under a
Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License
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For developing high-fidelity flight simulations, an accurate and complete representation of the aerodynamic characteristics of the aircraft is necessary. To obtain a realistic aerodynamic database, system identification methods can be used to describe the applied forces and moments acting on the aircraft. This study is based on simulated flight test data from a nonlinear simulation of the F-16 aircraft. It is demonstrated that the complete set of aerodynamic coefficients can be reconstructed from the flight test data. Thrust forces and moments are obtained from ground tests. A practical system identification methodology based on the iterative equation error method to determine the nonlinear aerodynamic and engine thrust models in the absence of engine manufacturer data is developed. The estimated values obtained using the method are compared with the actual parameter values. A mathematical engine model that can be used to estimate the thrust force for any flight condition is also developed. The findings demonstrate that the proposed method yields accurate results. The developed methodology is well-suited for the identification of isolated aerodynamic drag and lift coefficients and the thrust model.
Subject Keywords
flight modelling
,
flight simulation
,
iterative equation error method
,
parameter identification
,
system identification
URI
https://hdl.handle.net/11511/108732
Journal
Aerospace
DOI
https://doi.org/10.3390/aerospace11010008
Collections
Department of Engineering Sciences, Article
Citation Formats
IEEE
ACM
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MLA
BibTeX
M. Millidere, F. Akgül, M. K. Leblebicioğlu, and J. F. Whidborne, “Development of Aerodynamic and Propulsion Models Using the Iterative Equation Error Method,”
Aerospace
, vol. 11, no. 1, pp. 0–0, 2024, Accessed: 00, 2024. [Online]. Available: https://hdl.handle.net/11511/108732.