Abstract
This study presents the results of experimental research and numerical calculations regarding models of a typical torsion box fragment, which is a common thin-walled load-bearing structure used in aviation technology. A fragment of this structure corresponding to the spar wall was made using 3D printing. The examined system was subjected to twisting and underwent post-critical deformation. The research was aimed at determining the influence of the printing direction of the structure’s individual layers on the system stiffness. The experimental phase was supplemented by nonlinear numerical analyses of the models of the studied systems, taking into account the details of the structure mapping using the laminate concept. The purpose of the calculations was to determine the usefulness of the adopted method for modeling the examined structures by assessing the compliance of numerical solutions with the results of the experiment.
Highlights
In aviation technology, due to the very specific nature of the considered objects, certain standards that affect the design processes and operational assumptions have been formed
For different material solutions, such as composites or printed structures, the mentioned phenomenon strongly depends on many additional factors and constitutes a new problem, which must be precisely described with the results of suitable research, in order to fulfill all demands and regulations related to the creation of aircraft structures
This paper presents the results of comparative experimental studies of a typical fragment of an aircraft load-bearing structure, operating in the range of post-critical loads and undergoing large deformations
Summary
Due to the very specific nature of the considered objects, certain standards that affect the design processes and operational assumptions have been formed. Due to the necessity of minimizing the mass of an object, the loss of stability of the skin under operating conditions is permissible, as long as this phenomenon has an elastic character and occurs locally, i.e., within the segment of the skin and limited by skeletal elements [3,4]. The problem of the loss of stability of thin-walled load-bearing components has been widely examined for structures based on isotropic materials, such as metals. For different material solutions, such as composites or printed structures, the mentioned phenomenon strongly depends on many additional factors and constitutes a new problem, which must be precisely described with the results of suitable research, in order to fulfill all demands and regulations related to the creation of aircraft structures
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