Procedimento multidisciplinar de análise de tensões em componentes estruturais de asas de RPAs

Abstract

Remotely piloted aircraft, RPA, have a growing variety of applications over the past decades. During flight, such aircrafts are subjected to distributed aerodynamic loads that act on the aerodinamic center, respectively, lift, drag and pitching moment. The present study offers a methodology for structural stress analysis of RPA’s wings components under distributed aerodynamic loads in critical flight conditions. Therefore, a routine was built using Matlab to build the combined envelope of gust and maneuvers, to identify the critical flight conditions and to distribute the aerodinamic loads, partially automated. Also, a procedure was developed for the replacement of the distributed loads for concentrated loads automatically generated in a Python routine. Once the pre-process of the study model is completed (an RPA designed for Aerodesign) using the graphical interface of finite element software ABAQUS/CAE, the routine in Python is reproduced in its programming interface, and a static analysis is requested. Finally, during post-processing, the maximum and minimum stresses acting on the structural components of the half-wing are evaluated according to the failure criterion of the Maximum Normal Stress for anisotropic fragile materials.