Host: The Japan Society of Mechanical Engineers
Name : [in Japanese]
Date : September 03, 2017 - September 06, 2017
This paper shows a theoretical formulation of attack angle of the wing twist morphing structure considering its skins and validation of the formula through numerical simulations. In our previous study, we have proposed a concept of wing twist morphing structure using a double-tube cylinder. By applying the double-tube cylinder as the spar, we can change the ratio of twist-angle per each section arbitrarily to enhance their flight performance in accordance with their various flight conditions. The double-tube cylinder is composed of inner-spar and outer-spar. They are connected at the ends of the wing-tip side. The inner-spar transmits the torque from the motor which connected at the wing-root side to outer-spar. The outer-spar is the shape variable member having open- and closed-section. Also we have developed the design method and confirmed the validation of it through twisting experiment. However, the skin was not taken into consideration in the previous design method. Therefore, we modified the previous formula and take the effect of skins into account. This structure is required to be twistable, therefore the skin has a slit at the trailing edge to decrease twisting rigidity and soft materials are applied to fill the inside of the skins in order to enhance their bending rigidity.
