Keisuke Otsuka

Abstract Absolute nodal coordinate formulation (ANCF) is a nonincremental nonlinear finite element procedure that has been successfully applied to the large deformation analysis of multibody systems for more than two decades. Although a comprehensive review on ANCF was conducted by Gerstmayr et al. (2013, “Review on the Absolute Nodal Coordinate Formulation for Large Deformation Analysis of Multibody Systems,” J. Comput. Nonlinear Dyn., 8(3), p. 031016), significant theoretical developments have

In this paper, a deployment simulation model for next-generation aerospace structures, such as satellite solar panels and deployable wing aircraft, is proposed. The model utilizes finite plate elements based on absolute nodal coordinate formulation that has many advantages, namely, a constant mass matrix, zero Coriolis and centrifugal forces, a simple description of constraint conditions, and applicability of large elastic deformation. However, two problems have prevented the plate element from

Slender deployable wings have attracted interest for use in Mars, Titan, and high-altitude flights. Such wings are composed of multiple bodies connected by hinge joints and can be deployed or folded spanwise during flight. A deployment simulation model is required for their design. This paper proposes a multifidelity multibody modeling method that uses a new asymmetrically gradient-deficient absolute nodal coordinate beam element. The proposed method addresses the drawbacks of conventional eleme

Abstract High aspect ratio wings are potential candidates for use in atmospheric satellites and civil aircraft as they exhibit a low induced drag, which can reduce the fuel consumption. Owing to their slender and light weight configuration, such wings undergo highly flexible aeroelastic static and dynamic deformations that cannot be analyzed using conventional linear analysis methods. An aeroelastic analysis framework based on the absolute nodal coordinate formulation (ANCF) can be used to analy

A nonlinear aeroelastic analysis framework for high-aspect-ratio wings that includes the aerodynamic effects of propellers is described. The high computational cost required for modeling aerodynamic interaction between the wing and propeller wake is reduced by taking advantage of the relatively slow dynamics of the wing. Consequently, the propeller wake is modeled as a straight vortex cylinder that does not require a computationally expensive wake updating process. By leveraging the smallness of

Geometrically nonlinear strain-based beam formulation has the potential to analyze flexible slender components in multibody systems efficiently owing to the minimum number of variables and constant stiffness matrix. The objective of this study is to develop a multibody dynamic analysis framework based on the strain-based beam formulation. To this end, we describe the constraint equation using the vector variables of the absolute nodal coordinate formulation that exhibits a velocity-transformatio