ANALYSIS OF THE STRESS-STRAIN STATE (SSS) OF AILERONS FROM POLYMER COMPOSITE MATERIALS (PCM) USING THE FINITE ELEMENT METHOD (FEM)
Abstract
The use of composite materials in modern aviation requires, at the early stages of designing, close collaboration between designers, tough engineers and technologists. This is primarily due to the anisotropic (in the general case) properties of composite materials. Weight optimization of PCM assemblies and parts is a complex multi-parameter task, including: – selection of material with desired properties; – the formation of a sandwich package with the orientation of the monolayers, in accordance with the fields of the tensors of the main flows; – providing static strength and stability loss analysis; – selection and development of a technological process, etc., etc. In the present work, the analysis of the SSS of one of the units of the aircraft at the stage of modifying the existing structure in accordance with the decision on the replacement of metallic materials with polymer composite materials is carried outThe calculation of SSS was carried out in the MSC software system. Software at the stage of issuing working design documentation. Positive excesses of strength are obtained using fracture criteria for PCM by linearly static analysis, analysis taking into account geometric nonlinearity and analysis for buckling. SSS is received for flight cases of loading and parking cases of loading (action of wind load). Based on the analysis, it was decided to develop a test program of samples to confirm the physical properties of materials and packages composite materials. Also in the future, life tests will be carried out to confirm the design life. Subsequently, the work will be accompanied by an analysis of SSS on the FEM at the stages of sample testing, static and life tests.
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