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...

The aerodynamic simulations of wind turbines are typically carried out using a steady inflow condition. However, the aerodynamics and aeroelasticity turbine blades can be significantly affected by wakes due to environmental conditions or presence neighbouring turbines. In this paper, effects flow unsteadiness on rotor investigated. It is found that wake have an impact field around it could also...

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...

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...

Our objective is to develop a nonlinear aerodynamic and nonlinear structural interaction (NANSI) methodology as an expedient aeroelastic tool to handle continuous dynamic motion of morphing vehicles/wings throughout the flight regimes of subsonic to transonic speeds. The proposed morph vehicles for method demonstration is the Lockheed Folding wing (the Folding wing). Preliminary results on Flut...

Within the basic framework of an existing anisotropic thin-walled beam model, a cou-ple of non-classical effects are further incorporated and the model thereby developed isvalidated. Three types of lay-up configurations, namely, the cross-ply, circumferentiallyuniform stiffness (CUS), and circumferentially asymmetric stiffness (CAS) are investi-gated. The solution methodology is...

In this paper we suggest some algorithms for the fluid-structure interaction problem stated using a domain decomposition framework. These methods involve stabilized pressure segregation methods for the solution of the fluid problem and fixed point iterative algorithms for the fluid-structure coupling. With one single loop the solution of the coupled system tends to the one of the strongly coupl...

Advances of the analytical, numerical, experimental and field-measurement approaches in wind engineering offers unprecedented volume data that, together with rapidly evolving learning algorithms high-performance computational hardware, provide an opportunity for community to embrace harness full potential machine (ML). This contribution examines state research practice ML its applications engin...

During the process of span extension for an aircraft wing equipped with a telescopic morphing mechanism, aspect ratio increases, and hence, geometrical nonlinearities might become more significant. In this regard, paper aims to investigate effect structural nonlinearity on aeroelasticity wings using exact fully intrinsic equations first time. Furthermore, effects various parameters such as thru...