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- Article name
- Analysis of edge effects and main stress-strain state of structurally-anisotropic aircraft panels comprising composite materials in refined theory
- Authors
- FIRSANOV V. V., , K906@mai.ru, Moscow Aviation Institute (National Research University), Moscow, Russia
GAVVA L. M., , rva101@mail.ru; nio1asp@mail.ru, Moscow Aviation Institute (National Research University), Moscow, Russia
- Keywords
- panels made of composite materials / panels made of isotropic materials stiffened with composite bundles / eccentric longitudinal and lateral set / edge effects / main stress-strain state
- Year
- 2021 Issue 1 Pages 3 - 9
- Code EDN
- Code DOI
- 10.52190/2073-2562_2021_1_3
- Abstract
- The mathematical model relations for the investigation of the edge effect influence on the slowly changing main stress-strain state (SSS) of structurally-anisotropic panels are proposed. The panels are made from composite (PCM) and isotropic materials stiffened with composite bundles. The equilibrium eighteenth and eighth order equations are designed with the different degree of the mathematical model refinement for a stiffening rib being torsioned under one-sided contact with the skin. The influence of the structure parameters on the level of displacements and stresses has analyzed. The possibility of the mathematical model simplification in order to apply the results for the design practice of structurally-anisotropic panels comprising composite materials for advanced aircraft products is validated.
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