TY - GEN

T1 - Modeling and identifying dynamic derivatives of a delta-wing aircraft using gaussian basis functions

AU - Kai, Daiki

AU - Sugiura, Hiroki

AU - Tezuka, Asei

N1 - Publisher Copyright:
© 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

PY - 2021

Y1 - 2021

N2 - An aerodynamic model and its identification method for investigating the variations of the pitch dynamic derivatives of a delta-wing aircraft model with respect to the angle of attack (AOA) were proposed in this study. Wind tunnel tests were conducted during two maneuvers: steady pitch sweep and pitch sweep with an overlaid 1 Hz pitch oscillation. To subtract the forces and moments that act under no-wind conditions from balance data during wind tunnel tests, no-wind forces and moments were modeled using Gaussian basis functions. The extracted net aerodynamic forces and moments were processed to model and identify its characteristics using the dynamic derivative model. By applying Gaussian basis functions to the representation of the dynamic derivatives, the model was able to express the dynamic derivatives that vary nonlinearly with the AOA. The identification was conducted using the regression analysis. The identified dynamic derivative due to the pitch rate exhibited a positive value in several AOA regimes; on the other hand, the dynamic derivative due to pitch acceleration exhibited a negative value over the entire AOA range of −5° to 20°. With respect to the pitching moment coefficient, the root mean square (RMS) value of the deviation between the proposed dynamic derivative model and wind tunnel test data was 0.0124 at 0° AOA. The RMS value of the deviation increased as the AOA increased, reaching 0.0869 at 17.4° AOA.

AB - An aerodynamic model and its identification method for investigating the variations of the pitch dynamic derivatives of a delta-wing aircraft model with respect to the angle of attack (AOA) were proposed in this study. Wind tunnel tests were conducted during two maneuvers: steady pitch sweep and pitch sweep with an overlaid 1 Hz pitch oscillation. To subtract the forces and moments that act under no-wind conditions from balance data during wind tunnel tests, no-wind forces and moments were modeled using Gaussian basis functions. The extracted net aerodynamic forces and moments were processed to model and identify its characteristics using the dynamic derivative model. By applying Gaussian basis functions to the representation of the dynamic derivatives, the model was able to express the dynamic derivatives that vary nonlinearly with the AOA. The identification was conducted using the regression analysis. The identified dynamic derivative due to the pitch rate exhibited a positive value in several AOA regimes; on the other hand, the dynamic derivative due to pitch acceleration exhibited a negative value over the entire AOA range of −5° to 20°. With respect to the pitching moment coefficient, the root mean square (RMS) value of the deviation between the proposed dynamic derivative model and wind tunnel test data was 0.0124 at 0° AOA. The RMS value of the deviation increased as the AOA increased, reaching 0.0869 at 17.4° AOA.

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M3 - Conference contribution

AN - SCOPUS:85100272313

SN - 9781624106095

T3 - AIAA Scitech 2021 Forum

SP - 1

EP - 10

BT - AIAA Scitech 2021 Forum

PB - American Institute of Aeronautics and Astronautics Inc, AIAA

T2 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021

Y2 - 11 January 2021 through 15 January 2021

ER -