Optimization of wing parameters to achieve minimum weight at defined aerodynamic loads

The paper presents the method suitable for optimization of parameters and applied to design aircraft subassemblies on the example of a swept wing. It outlines the assumptions that are necessary to develop a mathematical model and describes constraints that served as the basis to develop an algorithm and describe the corresponding procedures in the GRIP (Graphics Interactive Programming) language that is a part of the CAD/CAM/CAE Unigraphics system. The further part of the study comprises discussion how the wing parameters and the mass functional are affected by the rigidity constraints and strength constraints. The algorithm for designing aircraft components was finally developed with inputs to the multi-criteria design process ``Web Modelling'' of an aircraft body. The study also includes initial assumptions to algorithms originally developed by the author and dedicated to the modelling of components incorporated into aircraft structures.