A new experimental wind tunnel test-bed has been developed for the study of limit cycle oscillations induced by control surface freeplay. thorough examination several factors affecting is presented—starting from a reference configuration, effect changes in inertia and stiffness, time-varying gap size, gravitational loading, aerodynamic preload due to an angle attack. Both time-marching simulations describing functions analytical methods have used understand measurements capability capture...

Aeroelasticity in the transonic regime is challenging because of strongly nonlinear phenomena involved formation shock waves and flow separation. In this work, we introduce a computationally efficient framework for accurate aeroelastic analysis. We use dynamic mode decomposition with control to extract surrogate models from high-fidelity computational fluid dynamics (CFD) simulations. Instead identifying full flowfield or focusing on global performance indices, directly predict pressure...

Accurate and efficient aeroelastic models are critically important for enabling the optimization control of highly flexible aerospace structures, which expected to become pervasive in future transportation energy systems. Advanced materials morphing wing technologies resulting next-generation systems that characterized by highly-coupled nonlinear interactions between aerodynamic structural dynamics. In this work, we leverage emerging data-driven modeling techniques develop accurate tractable...

Limit cycle oscillations (LCO) are of great interest for aeronautic engineers. They may strongly affect performance and life aeroservoelastic systems. For quite some time, studies have focused on increasing the understanding physics behind freeplay-induced LCOs, striving to find general rules, particularly, if possible, certification purposes. However, few reproduced experimentally gap sizes required by regulatory agencies, no experimental tackled dynamically time-varying nonlinearities. In...

The effects of multiple control surface freeplay nonlinearities on the aeroelastic behavior an elastic wind tunnel model a full aircraft configuration are explored. work follows earlier works by authors that explored experimentally nonlinear phenomena and limit cycle oscillation due to freeplay. Initially, single nonlinearity was studied several tests components configuration. extension is reported here. complete described together with measurement system developed for tests. Results...

Current research efforts in aeroelasticity aim at including higher fidelity aerodynamic results into the multi-disciplinary simulation environments. In present effort, an updated Python-based Fluid–Structure Interaction framework has been included SU2 code to allow for efficient and fully open-source simulations of detailed aeroelastic phenomena. The method provides a powerful easily approachable environment. developed software assessed against three test cases increasing complexity, coming...

Flexible wings pose a considerable modeling challenge, as they involve highly coupled and nonlinear interactions between the aerodynamic structural dynamics.In this work, we provide an open source code framework, unifying recent data-driven methods that extend dynamic mode decomposition with control (DMDc) to model aeroelasticity of flexible wings.Our framework consists (1) fully parametrized wing model; (2) fluid-structure interaction (FSI) solver couples detailed finite element structure...

View Video Presentation: https://doi.org/10.2514/6.2023-2235.vid Morphing wing devices based on the active camber concept can improve aircraft performances in take-off and landing maneuvers. In this paper, a multi-level optimization procedure has been applied to design of morphing Droop Nose, framework Clean Sky 2 REG-IADP AIRGREEN project. The adopted deals with multi-disciplinary aspects design, testing, validation phases. Starting from initial requirements, full-scale prototype achieved,...

Abstract A new experimental wind tunnel test-bed has been developed for the study of limit cycle oscillations induced by control surface freeplay. Studies effects a single nonlinearity, made possible horizontal tail plane, are described here. Several considered, starting from reference configuration: effect changes in inertia and stiffness, time-varying gap size, an aerodynamic preload due to angle attack. Both time marching simulations describing functions analytical methods have used...

Abstract Unshrouded industrial centrifugal compressor impellers operate at high rotational speeds and volume flow rates. Under such conditions, impeller blade excitation is dominated by frequency interaction with stationary parts, i.e., vaned diffusers or inlet guide vanes. In a previous study conducted on two full compression units of the original equipment manufacturer (OEM), authors identified, characterized, quantified resonant vibration caused blades rotating stall cells during severe...

Highly flexible wing may experience large deflection such that the linear analysis methods are not valid anymore. The results obtained with classical aeroelastic solution strongly affected by experienced during flight and they provide wrong results, jeopardizing aircraft. Large affects static e.g. trim, but pre-stress effect impacts on modal base used to evaluate dynamic response flutter behavior.

The results of wind tunnel flutter tests with an aeroservoelastic model a full airplane configuration are presented. has two mechanisms in the operative range tunnel. With proper design active control laws, it is possible to reach and experimentally identify second mechanism without modifying its behavior. A modified controller can both expand flight envelope 20% airspeed above mechanisms.

Abstract Unshrouded industrial centrifugal compressor impellers operate at high rotational speeds and volume flow rates. Under such conditions impeller blade excitation is dominated by frequency interaction with stationary parts, i.e. vaned diffusers or inlet guide vanes. In a previous study conducted on two full compression units of the original equipment manufacturer (OEM), authors also identified, characterized quantified resonant vibration caused blades sub-synchronous rotating stall...

Aeroelasticity in the transonic regime is challenging because of strongly nonlinear phenomena involved formation shock waves and flow separation. In this work, we introduce a computationally efficient framework for accurate aeroelastic analysis. We use dynamic mode decomposition with control (DMDc) to extract surrogate models from high-fidelity computational fluid dynamics (CFD) simulations. Instead identifying full field or focusing on global performance indices, directly predict pressure...

Abstract. A new experimental wind tunnel test-bed has been developed for the study of limit cycle oscillations induced by control surface freeplay. Studies effects a single nonlinearity, made possible horizontal tail plane, are described here. Several considered, starting from reference configuration: effect changes in inertia and stiffness, time-varying gap size, an aerodynamic preload due to angle attack. Both time marching simulations describing functions analytical methods have used...

Abstract. A computational framework for thermo-elastic homogenization of polycrystalline materials is proposed. The formulation developed at the crystal level and it based on explicit Voronoi representation micro-morphology. equations are formulated in an integral form numerically treated through boundary element method. presence volume integrals, induced by inherent physics coupling, addressed a Dual Reciprocity Method (DRM), which allows recasting terms integrals only. methodology applied...

Current research efforts in aeroelasticity aim at including higher fidelity aerodynamic results into the simulation frameworks. In present effort, Python--based Fluid--Structure Interaction framework of well known SU2 code has been updated and extended to allow for efficient fully open-source simulations detailed aeroelastic phenomena. The interface standardised easier inclusion other external solvers comunication scheme between processors revisited. A native solver introduced solve...