Research On Mechanical Properties Of High Temperature Resistant Resin Matrix Composite Materials And Their Application In Rocket Body Structur

Carbon fiber reinforced resin matrix composites are widely used in aerospace structural components due to their advantages of high strength,lightweight,fatigue resistance,high temperature resistance,and flexible structural design.The use of composite materials in structural components can effectively reduce the weight of the structure on the premise of meeting the use requirements.Therefore,the application of composite materials in aerospace structures is an important symbol to measure the progressiveness of aerospace structures.With the increasingly harsh flight environment of aerospace vehicles,higher requirements are put forward for the high-temperature resistance of aerospace vehicle structural products,and the importance of temperature resistance of composite structures is becoming increasingly prominent.In this paper,First,the newly developed T700/Si BP inorganic hybrid composite was tested for high temperature mechanical properties to explore the effect of temperature on the tensile properties,bending properties and interlaminar shear strength of T700/Si BP inorganic hybrid composite laminates.Compared with the high-temperature mechanical properties of the third generation polyimide resin matrix composite MT300/KH420,the resin matrix composite with high retention rate of high-temperature mechanical properties was selected to complete the follow-up research work.Then,The third generation carbon fiber/polyimide resin matrix composites MT300/KH420 were studied.Based on the shell segment instability theory,considering factors such as structural thermal deformation and material high-temperature performance attenuation,the axial compression instability analysis of composite cylindrical shells with different types of stiffeners under different temperature loads is conducted to explore the impact of different types of stiffeners and different temperatures on the bearing performance of cylindrical shells.Finally,based on the background of a launch vehicle interstage development mission,and based on structural design requirements such as structural appearance requirements,opening requirements,and load requirements,two preliminary design schemes of metal shell stiffened and composite material stiffened shells are proposed,and detailed designs of the two configurations are carried out.Use finite element analysis software to analyze the strength and instability of the interstage structure design scheme,and conduct reinforcement design for the weak parts of the structure.Provide the final design scheme and main mechanical performance parameters of the interstage segments of two structural configurations,and discuss them,and provide the optimal structural configuration that meets the structural design requirements.