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 plateelement from being utilized for simulation. The first problemisthe absenceofthe deployment system model composed of the actuator torque considering compound rotation angles, holding/releasing, and latching mechanismsinthe plate element.Adeployment system model that addresses this needistherefore 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 isdue 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.
ASJC Scopus subject areas
- Aerospace Engineering