A Research On Rapid Optimization Method Of Composite Wing-panel Structure

The application proportion of composites has become an important advanced standard for modern airliners. The structure of stiffened panel can effectively improve the structural-load-carrying capacity and anti-buckling-instability and reduce the weight, so that it is generally used in composite wing structure. Because the composite materials are typically anisotropic, it brings up the difficulties in design especially rapid design. Nowadays, the optimization of stiffened panel usually use FEM detail model or agent model, it brings large calculated amount and poor efficiency which lead to a long design period. Therefore, the research on a rapid design method of composite wing-panel is valuable in engineering.A method of rapid analyzing stiffened panels was introduced, which can be applied to different section form of stiffened panel. Based on the calculation methods of global buckling, torsional buckling and local buckling, a stability optimization design criteria for stiffened panel was created. The stiffened panel designed with the design criteria have high structural efficiency. The accuracy of the method was testified by comparing the results obtained respectively by the method and FEM software.Aiming at a specific light-weight utility airplane, The method was used to rapidly design the structure of the wing panel. The aerodynamic loading was calculated and the material and layout was choose. For the preliminary design result, the joints which have a major influence was rapidly design and NASTRAN was used to do further detail optimization design which can further reduce the weight of the wing. At last the design requirements can be better satisfied.