Aeroelastic model and analysis of an active camber morphing wing

Morphing aircraft structures usually introduce greater compliance into aerodynamic sections, and therefore will affect the aeroelasticity with potential risk of increased flutter. A low-fidelity model an active camber morphing wing its aeroelastic are developed in order to investigate critical speed by exploiting chord-wise dimension flexibility. Such a may be used for conceptual design, where low fidelity models explore optimise wide range configurations. The concept is implemented using continuous representation two-segment structure rigid segment deformable part. based on both steady unsteady models, so that different parameters can easily modified examine changes flutter solutions. Of particular interest ratio length chord, relative stiffness, as such operated part flap. By comparing results quasi-steady it shown gives more conservative prediction speed. In addition, responses phase space simulated show fundamental behaviour wing. It also compliant stabilise feedback control. This paper provides system-level insight through mathematical modelling, parameter analysis control dynamics applications camber.