In the German Aerospace Center, DLR, an internal project has been launched to investigate different UCAV configurations. One aspect, covered by the Institute of Aeroelasticity and the Institute of Aerodynamics and Flow Technology, is the wind tunnel test of a UCAV wing in subsonic and transonic flow. The model shall show measurable static aeroelastic deformations. Main goals of the tests will b...

This paper explores the robust control of large flexible wings when their dynamics are written in terms of intrinsic variables, that is, velocities and stress resultants. Assuming 2-D strip theory for the aerodynamics, the resulting nonlinear aeroelastic equations of motion are written in modal coordinates. It is seen that a system which experiences large displacements can nonetheless be accura...

SUMMARY Brief consideration of current approaches to the prediction of unsteady wing loading in mixed subsonic and supersonic flow shows a wide variety of method and a clear need for economy in transonic aerodynamic calculations for flutter clearance in subsonic flight. In support of measurements of steady and oscillatory pressure distributions on a particular wing, an approximate theoretical t...

New approaches to multidisciplinary design optimization have been developed and demonstrated in a NASA Langley funded project to look at a particularly challenging aeronautics problem – High Speed Civil Transport Aeroelastic Wing Design. In particular, the problem is how to incorporate key multidisciplinary information and knowledge as it becomes available. This problem results from such inform...

The exploitation of computational fluid dynamics for non linear aeroelastic simulations is mainly based on time domain simulations of the Euler and NavierStokes equations coupled with structural models. Current industrial practice relies heavily on linear methods which can lead to conservative design and flight envelope restrictions. The significant aeroelastic effects caused by nonlinear aerod...

Abstract It is known that the dynamic aeroelastic stability of T-tails dependent on steady aerodynamic forces at aircraft trim condition. Accounting for this dependency in flutter solution process involves correction methods doublet lattice method (DLM) unsteady aerodynamics, enhanced DLM algorithms, vortex (UVLM), or use CFD. However, improvements along with a commonly applied modal approach l...

The present paper introduces the sloshing effects on aeroelastic stability and response of flying wing configurations. Using reduced order model based data provided by computational fluid dynamics data, description slosh is introduced into an integrated modelling that accounts for both rigid elastic behaviour flexible aircraft. fully unsteady aerodynamics, modelled in frequency domain via doubl...

A flight test platform is designed to conduct an experimental study on the body freedom flutter of a BWB flying wing, and performed by using proposed platform. finite element model structural dynamics built, unsteady aerodynamics aeroelastic characteristics wing are analyzed doublet lattice method g-method, respectively. Based foregoing analyses, low-cost low-risk flying-wing manufactured. Then...

• The interaction between the transient flow and blade structure vibration in a modern low-pressure turbine is analysed using high-fidelity direct numerical simulation method. unsteady downstream wakes are highly influenced by vibration. vortex structures directly associated with Unsteady Reynolds Averaged Navier–Stokes (URANS) models not able to capture separation behaviour of flow. At least 5...

Abstract Aeroelasticity studies the static and dynamic interaction between structural deformation fluid forces. As a result, aeroelasticity is usually divided into three parts: aerodynamics, response, dynamics with statics as special case. Instabilities may occur to this (feedback) that lead failure and, even when no instability occurs, degradation or improvement of system performance. There ar...