SIZE OPTIMIZATION OF AIRCRAFT STRUCTURES

摘要

Structural optimization is currently a design methodology highly needed in advanced engineering and needless to say in aircraft design.In the paper a structural model that describes very precisely the rear part of an airplane fuselage is used to present the capabilities of size optimization.Two different problem formulation where defined. First only stress constraints were included in the problem. In a second problem stress and strain constraint were considered. In both cases a parametric study was carried out to find out the influence of different values of upper bounds of constraints in the optimal solution.