Vectoring Nozzle Vane Fluid-solid Thermal Coupling Values

During SRM(Solid rocket motor)'s working process, the gas transfers heat to propellant for keeping combusting and at the meanwhile heat is also transferred to the combustion chamber wall,nozzle,vane flake and some other components. Because of high-temperature gas, temperature of these components raced up and material strength decreases obviously. That is why when designing the component structure of SRM, we should start with actual strength of the components under heating condition. Moreover, gas transferring heat would cause an inhomogeneous distribution of inner temperature of the components, which could also be affected by the thermal stress loading role. As a result, rational and accurate structure design of SRM bases on considering the effect of heat transfer and doing rigorous heat transfer calculation.In this thesis, it is discussed about some type of solid rocket motor gas air-to-air missile rudder vectored nozzle. The method of heat transmission numerical analysis for FSI is adopted, mathematical model suitable for FSI heat transmission is established and I also use reasonable problem-solving technique, so simulation and analysis of solid domain temperature field such as vectored nozzle and gas vane flake and also gas rudder flow around flow field are accomplished. I select FSI surface temperature and Static-Pressure simulation result as the boundary conditions of Thermal-Structural coupling to analyze Thermal-Structural coupling stress for nozzle and gas vane flake in Ansys. It supports the constructive conclusions for structure design of RSM's nozzle and gas vane flake, thermal stress analysis and insulation protection design. The analysis conclusions correspond pretty well with the experimental results, and it has excellent project applicability.