A Numerical Investigation on Stress Modal Analysis of Composite Laminated Thin Plates

Because of the light weight and high strength, composite laminates have many advantages in aircraft structures; however, they are frequently subjected to severe dynamic loadings during flight. To understand properties laminated thin plates at stress scale, this paper studies modal analysis (SMA) by finite element method (FEM). Firstly, basic theory on SMA was given from classical displacement analysis. Secondly, a square plate numerically studied obtain some distribution laws mode shapes (SMSs) layup component perspectives. Then, based characteristics SMSs different plies, modified configuration conducted for possible lower magnitude more uniform distributions SMSs. Results indicate that ±45° layups can improve performance plate, without excessively decreasing frequencies. Such fact manifests critically vital reduction plates. Modal participation factor strain energy were evaluated assist determination critical modes. Lastly, aspect ratio design considered. Numerical investigation study serve as preliminary step perspective optimization laminates.