ASPECTS REGARDING INTERLAMINAR STRESS DISTRIBUTION ON THE COMPOSITE LAMINATED SKIN OF A TAIL ROTOR BLADE EXPOSED TO AERODYNAMIC FORCES

Abstract

In realizing a high-performance composite material, it is important to take into consideration all the factors that influence the structural response of the component when exposed to service conditions. Thus, in the case of the laminar skin of a composite tail rotor blade, the study of the stress distribution on each lamina is important, so that the optimal design can be chosen. The ACP Post module of the Ansys Workbench finite element software offers the possibility of visualizing the stress distribution on each lamina of the skin, as well as the value of the safety factor for multiple failure criteria.

Keywords

• helicopter tail rotor blade
• laminar composite materials