Deployment Simulation Using Absolute Nodal Coordinate Plate Element for Next-Generation Aerospace Structures

Abstract

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 being utilized for simulation. The first problem is the absence of the deployment system model composed of the actuator torque considering compound rotation angles, holding/releasing, and latching mechanisms in the plate element. A deployment system model that addresses this need is therefore proposed. The second problem is a long calculation time, which is highly undesirable because many parametric simulations are necessary for the deployment system design. The long calculation time is due to the strong nonlinearity of the plate element and many joint constraint conditions. To solve this problem, this paper introduces the mitigation of the nonlinearity, component mode synthesis, and velocity transformation into the plate element. The proposed model succeeds in simulating the deployment of the solar panel and deployable wing aircraft with a significant reduction of the calculation time.