The Integration Sviceability Research Of Heterogeneity Laminated Structure Transparent Material

Recent years, with the rapid development of aviation technology, more and more advanced composite material structures are application in aviation, aircraft windshield is a high-strength composite material. Aireraft windshield was a laminated glass, it's unit consists of two or more than two apparent materials with very high elasticity modulus, which was formed by bounding together an elastomeric Polymer with very low shear modulus, and between each material the thermal-expansion coefficient had the very great difference. Variation range is great of aireraft windshield surface temperature due to flight envirorunent and flight state,so the shear damage is easy appeared. Bird-strike other load are also happened.The research is based on the external conditions sviceability about laminated structure of the heterogeneity of transparent material aircraft windshield. based on each of the basic properties of materials, through the computer simulation to predict the overall structure of the aircraft windshield and laminated the surface of some of the basic performance and its performance in service conditions. All follows:Based with the test of physics testing about elastic modulus, shear modulus,thermal expansion coefficient. use to the finite element software ABAQUS achieve its process of simulation testing, through simulation analysis and programing, achieved the elastic modulus, shear model and the thermal expansion coefficient of the forecast about aircraft windshield.In the service conditions of the laminated structure of the aircraft windshield simulated the coupled thermo-mechanical performance, forecasting its service conditions in the most vulnerable to damage and destruction of the location of the laminated structure, token of the shear deformation and coordination of windshield aircraft. Reference tensile testing with the tensile load, predicted in the event of aircraft windshield before fracture, combined with the surface layer in response to the corresponding stress-strain relations.Use the critical failure criteria of energy , in the normal load to be aimed the windshield. Through the simulation analysis and programming calculated the laminated structure with different thickness and span, the largest energy absorption and the corresponding strength of each layers. According to the critical failure mode obtain the critical failure Concentration, the critical failure displacement, maximum absorption of energy and the plate strength of different thickness and span . Proposed the design direction of laminated plates structural optimizationAccording to the standard impact testing, through dynamic simulation of aircraft windshield forecasted the impact toughness values.Use the method of contours integral by finite element software ABAQUS predicted the fracture toughness value of mineral glass and organic glass in the type of I or II cracking.