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...

A series of wind tunnel model tests and theoretical analyses were conducted to investigate torsion excitation, response and vibration suppression of wind-excited buildings. An aeroelastic model for pure torsion vibration was developed and the aeroelastic test results were compared with those obtained by other Wind tunnel test techniques. The comparison and practice indicated that this type of m...

The aeroelastic response of a bird-damaged fan stage at the inlet of a high-bypass ratio turbofan engine is examined using a combined CFD/CSD model. ANSYS CFX is used for the computational fluid dynamic (CFD) calculations combined with the ANSYS Multifield (MFX) solver that couples ANSYS CFX with ANSYS Mechanical APDL to perform aeroelastic response calculations. The damaged fan sector consists...

This paper presents a study on the coupled aeroelastic/flight dynamic stability and gust response of a blendedwing-body aircraft that derives from the U.S. Air Force’s High Lift-Over-Drag Active (HiLDA) wing experimental model. An effective method is used to model very flexible blended-wing-body vehicles based on a low-order aeroelastic formulation that is capable of capturing the important str...

An aeroelastic analysis based on finite elements in space and time is used to model the helicopter rotor in forward flight. The rotor blade is represented as an elastic cantilever beam undergoing flap and lag bending, elastic torsion and axial deformations. The objective of the improved design is to reduce vibratory loads at the rotor hub that are the main source of helicopter vibration. Constr...

A rotor dynamic analysis method for the complex three-dimensional design blade was developed and applied to analyzing its aeroelastic stability. Based on medium-size deformation beam theory Hamilton principle, joint transfer matrix used in kinematic compatibility principle assembled finite element develop structural dynamics model. The BO105 validate this characteristic of analyzed detail. resu...

This paper presents an integrated flight dynamic modeling method for flexible aircraft that captures coupled physics effects due to inertial forces, aeroelasticity, and propulsive forces that are normally present in flight. The present approach formulates the coupled flight dynamics using a structural dynamic modeling method that describes the elasticity of a flexible, twisted, swept wing using...

The present research investigates the torsional aeroelasticity of the blade of an H-type vertical axis wind turbine subject to stall and post-stall conditions in various Reynolds regimes, which is experienced by the blade in a full revolution. In order to simulate the aerodynamics, a new model based on a combination of the Double Multi Streamtubes (DMST) model and the nonlinear multi-criteria C...

in the present paper, the aeroelastic stability of helicopter rotor blade is determined using aeroelastic frequency response function. the aeroelastic model of blade is obtained by combining dowell - hodges beam model with loewy unsteady aerodynamic theory which considers an unsteady wake beneath the rotor. equations are formed and aeroelastic frequency response functions are obtained by invert...

High-aspect-ratio wings present in very flexible aircraft can undergo large deformations, which results in significant changes in natural frequencies as well as in static and dynamic aeroelastic response. This geometric nonlinear behavior becomes an integral part of any aeroelastic analysis to be conducted in such class of vehicles. Aeroelastic scaling is an important way to study the aeroelast...