摘要: In aerospace structures such as the fuselage and blades of helicopters that are subjected to significant levels of noise and vibrations during their lifecycle, lightweight materials with high structural damping and practical flexu... 展开 In aerospace structures such as the fuselage and blades of helicopters that are subjected to significant levels of noise and vibrations during their lifecycle, lightweight materials with high structural damping and practical flexural performance are required. One of the best options for this is to employ sandwich structures with a structural foam core and a polymer matrix composite with a 45° fiber orientation. These sandwich structures are mostly used in the aerospace and automotive industries owing to their unique strength and stiffness. This study aims to focus on sandwich structures that can provide high damping values and reasonable flexural rigidity. For this purpose, woven carbon fibers-polymer matrix plies with 45° fiber orientations and foams with 10.7 mm and 49.8 mm thickness were selected as face sheets and cores, respectively to manufacture sandwich structures. To get further investigate the vibration characteristics of the structures, holes at some specified positions were created on the neutral axis of the sandwiches, with aim of not compromising the flexural rigidity values. 收起