ТОПОЛОГИЧЕСКАЯ ОПТИМИЗАЦИЯ ЭЛЕМЕНТОВ УЗЛОВ ЛЕТАТЕЛЬНОГО АППАРАТА

Abstract

The rapid development of additive production methods, which exclude technological limitations in the manufacture of aircraft parts due to their form complexity and strength requirements, dictates the need for effective methods for optimizing the topology of the part. On the example of the solution of the test problem of topological optimization of a loaded, cantilevered beam, the perspective of applying the proposed algorithm for reducing the weight of aircraft parts with preservation of their bearing properties is shown. The task of optimizing the topology of a loaded beam was considered in the Ansys Mechanical environment, the resulting solution was compared with the initial stress-strain state of the original beam geometry.is considered, and a verification strength calculation is performed.