Aeroelasticity is a critical consideration in the design of gas turbine engines, both for stability and forced response. Current aeroelastic models cannot provide highdelity aerodynamics in a form suitable for design or control applications. In this thesis low-order, highdelity aerodynamic models are developed using systematic model order reduction from computational uid dynamic (CFD) methods. ...

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...

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...

Active stabilisation of the 2 and 3 degrees-of-freedom (DoF) aeroelastic wind sections with structural nonlinearities led to various control solutions in the recent years. The paper proposes a control design strategy to stabilise the 3 Dof aeroelastic model. It is assumed that the aeroelastic model has uncertain parameters in the trailing edge dynamics and only one state variable, the pitch ang...

An integrated computational  uid dynamics (CFD) and computational structural dynamics (CSD) method is developed for the simulation and prediction of  utter. The CFD solver is based on an unsteady, parallel, multiblock, multigrid Ž nite volume algorithm for the Euler/Navier–Stokes equations. The CSD solver is based on the time integration of modal dynamic equations extracted from full Ž nite e...

Through aeroelastic modeling of membrane wings such as Leading Edge Inflatable (LEI) tube kites used in Airborne Wind applications, one can gain a better understanding of processes relevant for flight stability and performanceoptimization. Theaimof thisproject is toestablish abaseline for apartitionedaeroelastic solver suitable for membrane wings at high Reynolds numbers by coupling high fideli...

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...