Extreme climatic conditions

such as hot

cold and hot-humid environment

affect the bearing performance and the life expectancy of composite and metal hybrid structural components in aircraft

which have a great impact on the flight performance and safety of the aircraft.Due to the large coefficient of thermal expansion mismatch between the composite and metallic structures

the temperature change in the actual flight condition induces high thermal stresses in both composite component and metallic component.This additional stress would alter load transfer and internal stress distribution in fastened hybrids of composite and metallic structure.Thermal/mechanical behavior of the large-scale

multi-joint hybrid composite/metal structure was investigated experimentally in different temperature conditions

as well as bearing axial load under different temperatures.The internal stress distribution of different components and fasteners in hybrid composite/metal structure under different temperature and load conditions was obtained by the strain gage method.