Abstract
Morphing wing technology is to change the wing shape during flight. The technology has a potential to improve aircraft performance dramatically. One of the attractive morphing wings is the wing that can deploy or fold in the wing span direction. Such a morphing wing is called a deployable wing. The wing consists of several wing bodies jointed by hinges. A deployment actuator and a latching system are attached to the hinge. To obtain the good design of the deployable wing, the deployment simulation using a numerical model is necessary. We have proposed the numerical model comprising flexible multibody dynamics using absolute nodal coordinate formulation (ANCF) and unsteady aerodynamics. The model expresses the coupled motion of large aeroelastic deformation and large rigid body rotation. The model has a constant mass matrix, which means that there is no need to consider imaginary forces. However, it is difficult to model the deployment torque considering relative rotation angle between bodies because ANCF uses vectors expressed in a global coordinate system as nodal variables instead of rotation angles. This paper presents a modeling method to overcome this difficulty. Additionally, we model a lathing mechanism that is necessary for the deployment simulation. Finally, parametric deployment wing simulations are conducted to show the applicability of the model.
