In this work, the aeroelastic stability of an aerial refueling system is investigated. The formed by a classical hose and drogue, novelty our work inclusion grid fin configuration to improve its stability. unsteady aerodynamic forces on fins are determined using concept unit (UGF). For each UGF, computed Doublet-Lattice Method, complete calculated interfering factors obtained from wind tunnel m...

Modern aeroengine designs strive for peak specific fuel and thermal efficiency. To achieve these goals, engines have more highly loaded compressor stages, thinner aerofoils, blended titanium integrated disks (blisks) to reduce weight. These configurations promote the occurrence of aeroelastic phenomena such as flutter. Two important parameters known influence flutter stability are reduced frequ...

The undersigned hereby certify that they have read and recommend to the Faculty of Aerospace Engineering for acceptance a thesis entitled " Aeroelastic Roll Control for High Aspect Ratio Wings " Summary Modern aircraft tend to be light and slender. The high aspect ratio reduces the induced drag, increase fuel efficiency, and provide enough lift at low speeds. Therefore such wing types are used ...

This paper introduces an approach to effectively model the nonlinear aeroelastic behavior of fully flexible aircraft. The study is conducted based on a nonlinear strainedbased finite element framework in which the developed low-order formulation captures the nonlinear (large) deflection behavior of the wings, and the unsteady subsonic aerodynamic forces acting on them. Instead of merely conside...

A new method identifies coupled fluid-structure system with a reduced set of state variables is presented. Assuming that the structural model is known a priori either from an analysis or a test and using linear transformations between structural and aeroelastic states, it is possible to deduce aerodynamic information from sampled time histories of the aeroelastic system. More specifically given...

Several government/commercial oo-the-shelf modular software packages have been combined to perform static aeroelastic analysis and aerodynamic optimization of a generic high-speed civil transport, with the eventual goal of performing high-delity multidisciplinary optimization (MDO). Results obtained for the aeroelastic analysis and aerodynamic optimization cases are consistent with expectations...

This paper presents a static aeroelastic model and longitudinal trim model for the analysis of a flexible wing transport aircraft. The static aeroelastic model is built using a structural model based on finite-element modeling and coupled to an aerodynamic model that uses vortex-lattice solution. An automatic geometry generation tool is used to close the loop between the structural and aerodyna...

Recent enhancements to the development of CFD-based unsteady aerodynamic and aeroelastic reduced-order models (ROMs) are presented. These enhancements include the simultaneous application of structural modes as CFD input, static aeroelastic analysis using a ROM, and matched-point solutions using a ROM. The simultaneous application of structural modes as CFD input enables the computation of the ...

The development of a pilot-in-the-loop investigation into rotorcraft-pilot coupling are presented for three test campaigns which were conducted as part of GARTEUR HC(AG-16): rigid body; biodynamic and aeroelastic. For each campaign, the modelling activities and results are shown. PIO events were recorded during the rigid body test campaign, although not always in the expected vehicle axes. The ...