Static aeroelasticity computation of high-speed rotorcraft horizontal tail based on minimum F-norm correction panel method
Compared to the conventional configuration rotorcraft,the static aeroelastic effects have more obvious influence upon the high-speed rotorcraft horizontal tail.The engineering panel method is a widely used aerodynamic modeling approach in the field of static aeroelasticity numerical compu-tation.In order to improve the computation accuracy drawback of panel method,and meanwhile keep its intrinsic advantages in formulation simplicity and high efficiency,a novel minimum F-norm correction panel method is herein presented.By using a correction coefficient matrix derived from the CFD data of rigid and preset torsion models,there is subsequently an excellent agreement be-tween panel method and CFD for the aerodynamic loads acting on deformed horizontal tail.Based on the proposed correction panel method,and integrated with structural finite element model,the static aeroelasticicity numerical computation of high-speed rotorcraft horizontal tail is performed,demon-strating the applicability and effectiveness of the proposed method in static aeroelasticity analysis.
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