Effect of Directional Stiffness on Control Reversal Speed

Aeroelastic tailoring is basically the use of directional stiffness to achieve desirable changes in our aerodynamic parameters. In this research paper, the aileron reversal speed of a fighter aircraft has been evaluated by modelling and subsequent analysis of the wing in FEMAP. The static aeroelastic analysis has been carried out at Mach 0.0 and sea level conditions and aileron deflection of 1 degree. The model was simulated at different dynamic pressures one by one and the speed of aileron control reversal was evaluated by examining the stability derivatives in the result file of FEMAP. The material properties of the wing were now changed and laminate element with 2D orthotropic material was used and wing central region was now given this composite property. The whole process of finding the aileron control reversal speed was again carried out and the results were compared with the previous case. An increase in the reversal speed was observed. This comparison would allow us to better comprehend the use and significance of directional stiffness in influencing our aerodynamic parameters of an aircraft. In the end recommendations for future work are also presented.