Modeling the stiffness and strength of aerospace structural elements

摘要: The classical method for obtaining the stiffness of composite laminates is presented highlighting stretching, bending, and bending/stretching coupling behavior. resulting stresses and/or strains are then combined in failure criteria. Different criteria along with some their drawbacks. discussion extended to notched strength by briefly treating holes. Woven composites also introduced a brief overview methods obtain strength. Issues related defects such as porosity or delaminations that may be present aircraft parts discussed. chapter closes summary future trends grid-stiffened variable-stiffness structures.