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 the absolute nodal coordinate formulation (ANCF). ANCF 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 ANCF plate element from being utilized for simulation. The first problem is the absence of the deployment system model, including the actuator torque, holding/releasing, and latching mechanisms in the ANCF plate element. We therefore propose a deployment system model that addresses this need. The second problem is a long calculation time, which is fatal because many parametric simulations are necessary for the deployment system design. The long calculation time is due to the strong nonlinearity of the ANCF elastic force and many joint constraint conditions. To solve this problem, we introduce the mitigation of the nonlinearity, component mode synthesis, and velocity transformation into the ANCF 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.