Amirkabir University of Technology Amirkabir Journal of Mechanical Engineering 2008-6032 51 1 2019 04 21 Airplane Nonlinear Aerodynamic Model Identification in Spin Maneuver by Using Extended Multi Input Approach Airplane Nonlinear Aerodynamic Model Identification in Spin Maneuver by Using Extended Multi Input Approach 201 214 2656 10.22060/mej.2017.12359.5329 FA A. Mokhtari Department of Aerospace Engineering, Amirkabir University of Technology, Tehran, Iran M. Sabzeh Parvar Department of Aerospace Engineering, Amirkabir University of Technology, Tehran, Iran 0000-0002-8228-6000 Journal Article 2017 01 29 In this paper application of the multipoint aerodynamic model for parameter estimation in spin maneuver as a high-angle-of-attack and high-angular-rate fight regime was concentrated. The identification technique used to illustrate the approach is maximum likely hood with the equation error approach. The multipoint model comprises a set of new parameters describing the aerodynamic force distribution along individual surface components of the aircraft so using this method will be useful for spin aerodynamic modelling. The aim of this study is to demonstrate that this model allows coupling among the three force and three moment components, this means that the parameters associated with the six-component equations are thus treated simultaneously. Another advantage of this approach is that the model allows each individual force generating surface element of the aircraft to contribute independently to the total force and moment rather than some average of these contributions relative to the center of mass. The method is applied to measurements from spin fight test data conducted with a light general aviation aircraft and the results compared with conventional aerodynamic model. The results indicate that the method is capable of reproducing, with reasonable accuracy, the force and moment measurements obtained from a fight other than the one used in the parameter estimation. In this paper application of the multipoint aerodynamic model for parameter estimation in spin maneuver as a high-angle-of-attack and high-angular-rate fight regime was concentrated. The identification technique used to illustrate the approach is maximum likely hood with the equation error approach. The multipoint model comprises a set of new parameters describing the aerodynamic force distribution along individual surface components of the aircraft so using this method will be useful for spin aerodynamic modelling. The aim of this study is to demonstrate that this model allows coupling among the three force and three moment components, this means that the parameters associated with the six-component equations are thus treated simultaneously. Another advantage of this approach is that the model allows each individual force generating surface element of the aircraft to contribute independently to the total force and moment rather than some average of these contributions relative to the center of mass. The method is applied to measurements from spin fight test data conducted with a light general aviation aircraft and the results compared with conventional aerodynamic model. The results indicate that the method is capable of reproducing, with reasonable accuracy, the force and moment measurements obtained from a fight other than the one used in the parameter estimation. https://mej.aut.ac.ir/article_2656_1680e9fa7b4dd5d62ece800239bb53bd.pdf