Abstract
High aspect ratio wing (HARW) structures will deform greatly under aerodynamic loads, and changes in the stiffness will have a great impact on the flutter characteristics of such wings. Based on this, this paper presents an effective method to determine the effect of the stiffness on the flutter characteristics of HARWs. Based on the calculation theory of the mechanical profile of thin-walled structures, the torsional stiffness and bending stiffness of the wing are obtained through calculation. We use the fluid-structure coupling method to analyze the flutter characteristics of the wing, and we use our research results based on the corotational (CR) method to perform structural calculations. The load is calculated using a computational fluid dynamics (CFD) solver. The results show that, compared with the original wing, when the bending stiffness and torsional stiffness of the wing along the spanwise direction increase by 8.28% and 5.22%, respectively, the amplitude of the flutter decreases by approximately 30%. Increasing the stiffness in the range of 0.4 to 0.6 Mach has a greater impact on the flutter critical velocity, which increases by 12.03%. The greater the aircraft’s flight speed is, the more severe the stiffness affects the wing limit cycle oscillation (LCO) amplitude.
Highlights
The above research results have achieved their expected purpose, when considering the application of these research results in actual engineering, it is urgent to further consider the issue of computational efficiency
Barnes et al [32] conducted a study on the effect of stiffness on the laminar separation flutter based on an NACA0012 airfoil and considered the effect of the Reynolds number. e results show that the change in stiffness at any Reynolds number will have a greater impact on the laminar separation chatter, resulting in even more nonlinear aeroelastic responses
After studying the effective stiffness calculation method and flutter calculation method separately, we considered the serious effect of stiffness on the flutter of High aspect ratio wing (HARW). erefore, in this paper, an effective and practical stiffness calculation method and an efficient nonlinear flutter calculation method are used to study the effect of stiffness on the flutter characteristics of an HARW
Summary
Wing stiffness centers were calculated for different cross sections selected from root to tip. To use the stiffness calculation formula to calculate the wing crosssectional rigidity, the cross-sectional area and material needed to be equivalent, as shown in [3]. In the stiffness calculation process, to facilitate programming, we used equivalent methods to process the area and material of the cross section of the wing according to the force characteristics of the structure. When the geometric parameters of the three-part spars were increased by 16.7%, 25%, and 25%, the bending and torsional stiffness distributions of the two wings along the span were obtained as shown in Figures 4 and 5. When the geometric parameters of the spars increase simultaneously according to the ratio, the wing bending and torsional stiffness distributions in the span direction are not uniform, there are relatively large changes in the aileron section. Kutta method to perform the calculations more conveniently; the calculation results are more accurate and can be Section A
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
