The procedures to assess the critical aeroelastic state of an aircraft with the AESIM simulation method are described. The main innovation is the identification with MIMO-class methods which opens up possibilities for efficient usage of aeroelastic simulation methods. Experience with recent applications is reported. ANALYSIS OF COMPUTATIONAL AEROELASTIC SIMULATIONS BY FITTING TIME SIGNALS Micha...

The identification of nonlinear aeroelastic systems based on the Volterra theory of nonlinear systems is presented. Recent applications of the theory to problems in experimental aeroelasticity are reviewed. These results include the identification of aerodynamic impulse responses, the application of higher-order spectra (HOS) to wind-tunnel flutter data, and the identification of nonlinear aero...

The hypersonic aeroelastic and aerothermoelastic problem of a double-wedge airfoil typical cross-section is studied using three different unsteady aerodynamic loads: (1) third-order piston theory, (2) Euler aerodynamics, and (3) Navier-Stokes aerodynamics. Computational aeroelastic response results are used to obtain frequency and damping characteristics, and compared with those from piston the...

The Solar powered unmanned aircraft have a high-aspect-ratio wings because SPUAV must satisfy the requirement of long endurance and high lift-drag ratio. Therefore, the structure of SPUAV‘s wings are structurally very flexible. The very high flexible wing might have large deformation and many aeroelastic problems. In this paper have a static/dynamic aeroelastic analysis through CFD-CSD coupled ...

AbstrAct: The Operational Modal Analysis technique is a methodology very often applied for the identification of dynamic systems when the input signal is unknown. The applied methodology is based on a technique to estimate the Frequency Response Functions and extract the modal parameters using only the structural dynamic response data, without assuming the knowledge of the excitation forces. Su...

High-Altitude Long-Endurance (HALE) aircraft have wings with high aspect ratios. During operations of these aircraft, the wings can undergo large deflections. These large deflections can change the natural frequencies of the wing which, in turn, can produce noticeable changes in its aeroelastic behavior. This behavior can be accounted for only by using a rigorous nonlinear aeroelastic analysis....

This paper presents a recently developed computational tool for aeroelastic analysis of aircraft performance. The computational tool couples a vortex-lattice code, Vorview, with an aeroelastic model that computes wing structural deflections under a combined coupled bending-torsion motion. The aeroelastic model of the wing structure is based on a one-dimensional structural dynamic theory using s...

Lateral nozzle forces are known to cause severe structural damage to any new rocket engine in development. Currently there is no fully coupled computational tool to analyze this fluid/structure interaction process. The objective of this study was to develop a fully coupled aeroelastic modeling capability to describe the fluid/structure interaction process during the transient nozzle operations....

System identification methods for non-linear aeroelastic systems could find uses in many aeroelastic applications such as validating finite element models and tracking the stability of aircraft during flight flutter testing. The effectiveness of existing non-linear system identification techniques is limited by various factors such as the complexity of the system under investigation and the typ...

this study investigated the performance and aeroelastic characteristics of a wind turbine blade based on strongly coupled approach (two-way fluid structure interaction) to simulate the transient fsi1 responses of hawt2. aerodynamic response was obtained by 3d cfd-urans approach and structural response was obtained by 3d finite element method. aeroelastic responses of the blade were obtained by ...