A Research On Rapid Design Method Of Composite Wing-Panel

The application proportion of composites has become an important advanced standard formodern airliners. Because the composite materials are typically anisotropic with more designparameters, it brings up the difficulties in design especially rapid design. Therefore, the research onrapid design method of composite wing-panel is valuable in engineering.Wing panel usually use thin stiffened panels, with elastic support of stringers. The differentstringer-panel stiffness ratio has the different support efficiency in stiffened panel with a optimal valuein all the ratios. A rapid design method is proposed in this thesis for the layout deign of compositewing structures, which based on FEM creating composite stiffened panel’s initial buckling experiencecurve. The hierarchy optimized design method is frequently used in the wing optimized design. Onthe basis of stacking sequence of the laminated，we can use a box structure to simulate wing structureand parameter define the box. Then the dimensions of stringers can be calculated by the stringer-panelstiffness ratio (ratio of the area of stringer cross-section and wing panel cross-section). Then a lot ofFinite Element Model will be created by PCL with the variable of stringer-panel stiffness ratio and beanalyzed in bucking. The initial buckling experience curve in which the efficiency of stiffened panelis plotted against the stringer-panel stiffness ratio can be got. At last, the rapid design can be achievedby the initial buckling experience curve.