A Meshless Approach to Aeroelastic Simulations with Large Control Surface Deflections

摘要

One deficiency of most current aeroelastic codes is their inabilities to deal appropriately with control surface deployment. Though transpirations techniques. Can be used, they are only capable of handling very small deflection, as they ignore the actual non-linear changes of the geometry.The origin of the difficulties for the correct modeling of large control surface deflection is that they introduce shearing in the mesh at the place where the control surface meets the fixed part of the wing (seeFig.l). In this paper, we present a meshless approach to the aeroelastics immolation of aircraft involving large control surface deflections.We make use of the Reproducing Kernel Particle Method combined with the Streamline-Upwind Petrov-Galerkin method to discretize the flow. We introduce a transition layer toward a projected solution to enforce the slip boundary conditions on the structural surface. By appropriately combining several transitions layers, our method allows us to deal with arbitrary relative motions of Structural elements, such as flaps, control surfaces, or a separating external missile or reservoir. As the structure moves, some nodes may penetrate or come out of the structure and we show how they can be dynamically activated or deactivated. We illustrate our approach with a two-dimensional simulation of an airfoil with a flap performing a separation motion.