Micro Electro-thermal Temperature Field Of CFRP And Interfacial Damage Analysis

Due to the development of composites material and its outstanding performance, like high specific stiffness and specific module, composites material was used more wildly on the aircraft, especially in main structure. During the service, composites material on aircraft may subjected to different level of current, such as lighting(KA level),electrical devices(A level) and electrostatic cumulative(mA level). When current introduced to composites material Carbon Fiber Reinforce Polymer, CFRP, electrical charge transport on carbon fiber and the Joule effect leads to a temperature augmentation of carbon fiber. Heat flux will conduct in interface and resin and cause a temperature gradient inside of material. This paper calculates the internal temperature field and stress field of single fiber specimen and CFRP laminates plate by ABAQUS FEA software and experience. The results show that ABAQUS could predict accurately the steady state temperature field of single fiber composites. The thermal resistance of resin will cause the significant temperature difference between surface of specimen and carbon fiber. The local high temperature near carbon fiber will cause considerable axial thermal stress on carbon and will cause heat degradation and damage of resin near carbon fiber. For the CFRP laminates plate ABAQUS could also accurately predict the temperature field of composites, but the temperature difference inside the specimen is negligible. Short beam shear test and transverse tensile was done by INSTRON5982 for CFRP laminates subjected to different level of DC current. Microscopic fracture analysis combines with experiment result to study the impact of electro-thermal effect on composite interface. Results show that when electro-thermal temperature under curing temperature, performance of interface don't change, however when electro-thermal temperature exceed curing temperature performance of interface drop with the increase of DC current.