Development of aerodynamic and propulsion models using the iterative equation error method

Simple item page
dc.contributor.authorMillidere, Murat
dc.contributor.authorAkgül, Ferhat
dc.contributor.authorLeblebicioğlu, Kemal
dc.contributor.authorWhidborne, James F.
dc.date.accessioned2024-01-04T13:43:39Z
dc.date.available2024-01-04T13:43:39Z
dc.date.issued2023-12-21
dc.description.abstractFor 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.en_UK
dc.identifier.citationMillidere M, Akgül F, Leblebicioğlu K, Whidborne JF. (2023) Development of aerodynamic and propulsion models using the iterative equation error method. Aerospace, Volume 11, Issue 1, December 2023, Article number 8en_UK
dc.identifier.issn2226-4310
dc.identifier.urihttps://doi.org/10.3390/aerospace11010008
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/20604
dc.language.isoenen_UK
dc.publisherMDPIen_UK
dc.rightsAttribution 4.0 International*
dc.rights.urihttp://creativecommons.org/licenses/by/4.0/*
dc.subjectflight modellingen_UK
dc.subjectparameter identificationen_UK
dc.subjectflight simulationen_UK
dc.subjectsystem identificationen_UK
dc.subjectiterative equation error methoden_UK
dc.titleDevelopment of aerodynamic and propulsion models using the iterative equation error methoden_UK
dc.typeArticleen_UK
dcterms.dateAccepted2023-12-18

Files

Original bundle
Now showing 1 - 1 of 1
Thumbnail Image
Name:
Aerodynamic_and_propulsion_models-2023.pdf
Size:
885.22 KB
Format:
Adobe Portable Document Format
Description:
Download
License bundle
Now showing 1 - 1 of 1
No Thumbnail Available
Name:
license.txt
Size:
1.63 KB
Format:
Item-specific license agreed upon to submission
Description:
Download

Collections

Staff publications (SATM)