Flexible multibody dynamics using absolute nodal coordinate formulation with internal constraint equation

Abstract

Next-generation aerospace structures, such as deployable wing aircraft, consist of very flexible bodies connected by joints because they are required to be lightweight. In designing the structures, a deployment simulation considering the high flexibility and joint is necessary. Multibody dynamics with absolute nodal coordinate formulation (ANCF) is effective for the simulation. ANCF is a nonlinear finite element method that can easily describe flexible deformation and constraint joint equations. However, ANCF cannot be easily applied to complicated cross-sectional structures such as a wing. This is because the volume integral necessary for the elastic force derivation is difficult for complicated structural shapes. To solve this problem, we present an ANCF beam element with internal constraint equations (ICE). ICE restricts the non-dominant deformation. Consequently, a line integral can be used instead of the volume integral. We demonstrate that the ANCF-ICE beam element can describe the very flexible deformation of a complicated cross-sectional structure in a flying wing simulation.