Abstract This study is to investigate the stall flutter of high-speed rotating blade section small-scale blades subjected combined flap-lag motion. The work motivated by destructive flapwise vibrations blades. aeroelastic governing equations combine a spring-mass-damper equivalent structure and nonlinear aerodynamic model suitable for pure pitching resulting are solved linearization time-marchi...

Numerical simulation of aircraft’s flutter is rather expensive and time-consuming. In order to save expense and calculating time, we apply first-order approximate conditions to solve the unsteady transonic Euler equations coupled with aeroelastic equations. Assuming that the airfoil is thin and undergoes small deformation, we implement wall boundary conditions on nonmoving mean wall positions. ...

It is not easy for the system identification-based reduced-order model ROM and even eigenmode based reduced-order model to predict the limit cycle oscillation generated by the nonlinear unsteady aerodynamics. Most of these traditional ROMs are sensitive to the flow parameter variation. In order to deal with this problem, a support vector machineSVMbased ROM was investigated and the general cons...

Many authors have shown the potential mass savings that a ballute can offer for both aerocapture and entry. This mass savings could enhance or even enable many scientific and human exploration missions. Prior to flight of a ballute several technical issues need to be addressed, including aeroelastic behavior. This paper begins to address the issue of aeroelastic behavior by developing and valid...

A study of multidisciplinary design concerning the incorporation of aeroelastic tailoring, control surface blending, and active aeroelastic wing concepts is presented. The design process incorporates response surfaces, fast probability integration and modal-basis multidisciplinary design optimization to characterize the design space. The wing box skins of a representative fighter configuration ...

The unsteady, aerodynamically induced resonance of aircraft structures may lead to potentially destructive vibrations when left unaccounted for in flight control system design. Such aeroelastic modes are difficult to accurately predict analytically, and computational models require calibration, verification, and validation. The successful design of control systems that actively suppress aeroela...

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...

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...