Abstract. Theoretical and experimental suppression of aeroelastic instabilities by means of broadband passive targeted energy transfers has been recently studied. A single-degree-offreedom (SDOF) nonlinear energy sink (NES) was coupled to a 2-DOF rigid wing modeled in the low-speed, subsonic regime with quasi-steady aerodynamic theory. The nonlinear attachment was designed and optimized to supp...

Wind tunnel to Atmospheric Mapping (WAM) is a methodology for scaling and testing a static aeroelastic wind tunnel model. The WAM procedure employs scaling laws to define a wind tunnel model and wind tunnel test points such that the static aeroelastic flight test data and wind tunnel data will be correlated throughout the test envelopes. This methodology extends the notion that a single test co...

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...

The “reverse path” spectral method, a frequency domain based nonlinear system identification technique, is considered for identifying nonlinear aeroelastic models. The method is based upon a multi-input/multi-output spectral conditioning process that mutually uncorrelates the linear and nonlinear components of the system response. Conditioned frequency response estimates derived from this proce...

A decoupled fuzzy sliding-mode control for an aeroelastic system is derived. This aeroelastic dynamic system describes the nonlinear plunge and pitch motions of a wing section, using a single trailing-edge flap as the control input. The decoupled fuzzy sliding-mode control design method is proposed to simultaneously control both the plunge and pitch motions of the aeroelastic system. In this de...

The investigation of aeroelastic/aeroservoelastic stability through flight testing is an essential part of aircraft certification. The stability boundary prediction is especially difficult when the instability is associated with nonlinearities in the dynamics. An approach is presented for the characterization of the nonlinear dynamics by noniterative identification algorithms. Two different blo...

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...

This research combines Volterra theory and proper orthogonal decomposition (POD) into a hybrid methodology for reduced-order modeling of aeroelastic systems. The outcome of the method is a set of linear ordinary differential equations (ODEs) describing the modal amplitudes associated with both the structural modes and the POD basis functions for the fluid. For this research, the structural mode...