Analysis of Stresses in Helicopter Composite blade in Hovering Maneuver

The main purpose of this article is the structural analysis of a composite blade of a selected helicopter. In this study, the stresses on rotor's blades caused by centrifugal forces, lift, drag and torque are analyzed. The governing equations of the structure behavior and solving processes were carried out by MATLAB software, and simulation is carried out by ABAQUS software, and they are compared with each other. The program written for MATLAB is based on beam element theory and the computation of stress and displacement of considered elements of a blade, is one of the properties of the written code. In ABAQUS, the helicopter blade is simulated in various states such as composite and aluminum blade with/without web and composite blade with laminations in different angles. The results of the mentioned states are compared with each other and with the code and finally, the results are compared with reference article. Comparison between beam element results and ABAQUS simulation shows proper match. In order to optimize a composite blade, attention must be paid to factors such as, displacement and stress reduction and prevention of excess in weight, as by an increase in thickness of 45 and 90 degree laminates to 6.5 mm, maximum displacement would be 12.9 cm, and total weight of the structure would be 8 Kg.