In this work, the enhanced correction factor technique (ECFT) is modified for a subsonic wing–body interference model, which can consider forces on both lifting boxes and body elements of an idealized airplane, termed advanced ECFT method. A passenger aircraft model chosen as simulation longitudinal static aeroelasticity at transonic situation two-degree freedom, including α (angle attack) degr...

in this paper, a complete model of an electro hydraulic driven dry clutch along with its performance evaluation has elucidated. through precision modeling, a complete nonlinear physical and full order sketch of clutch has drawn. ultimate nonlinearities existent in the system prohibits it from being controlled by conventional linear control algorithms and to compensate the behavior of the system...

Abstract Composite structures have shown a prominent impact in the aircraft structural design. With an increasing shift towards incorporating more composite materials primary structure it is imperative to corresponding design tools simplify process. In present work, simplified implementation for optimization has been developed within DLR-AE (German Aerospace Centre, Institute of Aeroelasticity)...

In this paper, the flutter instability of a conventional two-stage axially moving telescopic UAV wing is investigated. To aim, and to be as close possible reality, effects temporal variation mass length, due movement stages their overlapping, along with morphing speed are considered for first time. The bending-torsional dynamics modeled by modifying Euler–Bernoulli beam theory take into account...

recently, a large amount of studies have been related to nonlinear systems with multi-degrees of freedom as well as continuous systems. the purpose of this paper is to optimize passive vibration absorbers in linear and nonlinear states for an euler-bernoulli beam with a nonlinear vibratory behavior under concentrated moving load. the goal parameter in the optimization is maximum deflection of t...

This study investigates the static instability of a cracked plate in subsonic airflow. The model is an inverted cantilever plate, where its leading edge free and trailing clamped. A mathematical crack developed using Dirac function, while Theodorsen aerodynamic mode applied for fluid force. To account angle discontinuity caused by cracks, Fourier expansion employed to transform form correspondi...

In this study the centre manifold is applied for reduction and limit cycle calculation of a highly nonlinear structural aeroelastic wing. The limit cycle is arisen from structural nonlinearity due to the large deflection of the wing. Results obtained by different orders of centre manifolds are compared with those obtained by time marching method (fourth-order Runge-Kutta method). These comparis...

This paper presents an investigation on the capability of gust load alleviation by normal microjet. The numerical method integrates unsteady Reynolds averaged Navier-Stokes (URANS) solutions, structural dynamic equations motion and Field Velocity Method. is verified for responses rigid elastic models. results microjet are validated against experimental previous data. Load control capabilities e...

in this study, the nonlinear optical properties and optical limiting performance of the silver nanoparticles (agnps) in distilled water are investigated. the nonlinear absorption coefficient of the colloid is measured by the z-scan technique. the optical limiting behavior of the agnp suspension is investigated under exposure to nanosecond laser pulses at 532 nm. the results show that nonlinear ...