任意のねじり角分布に設定可能な二重筒構造のＴＷＩＳＴ型モーフィング翼への応用と実証

抄録

The double cylindrical tube achieving an arbitrary twist distribution was applied to a spar of a twist morphing structure and the applicability was demonstrated through a twisting experiment and a wind tunnel test. In the previous study, we developed the double cylindrical tube which achieves an arbitrary twist distribution and its basic theory has been derived. In this study, we developed and fabricated a wing twist morphing structure of which spar was the double cylindrical tube. Then a theoretical formulation for the twist angle of the wing twist morphing structure considering its skin was derived. Some experiments were carried out and it was confirmed that the specimen could be twisted to the target twist distribution under wind loads (wind speed was about 12 m/s. Furthermore, the specimen could be twisted regardless of the twisting direction, and the maximum error of the twisting angle was 18.1% at the wing tip. We also evaluated aerodynamic data, and calculated aerodynamic coefficients for each angle of attack. These experimental results demonstrate the applicability of the double cylindrical tube to wing twist morphing structure and reveal that the developed morphing structure can contribute to the enhancement of flight performance by twisting itself.