Under Complex Loads Of Solid Rocket Motor Design Optimization Of Stress Relief

Solid propellant rocket motor is widely used in missile and rocket weapon system, which technical level directly reflects the national defense science and technology strength of a country. With the performance and the cost of weapon system rising, higher requirements are put forward to security and maintenance of solid rocket motor. So far, adherent casting and free filling are two main forms of propellant. Due to poor bearing capacity of solid propellant, the propellant of adherent casting solid rocket motor is easy to crack and to debond under complex load, which safety and reliability is badly influenced. So, the study on the mechanical response of adherent casting solid rocket motor has become a long-term important task of structural integrity research of solid rocket motor.A300mm adherent casting solid rocket motor was taken as the background in this paper. And the research on mechanical response of the simple hole grain and star grain was carried out.temperature shock test and relative numerical simulation for adherent casting solid rocket motor formed simple hole grain and star grain were implemented. The distribution of temperature field and stress field of propellant was analyzed. And the influence of structure parameters on the mechanical response of the propellant was studied. It is verified that the numerical simulation results accorded with the experimental results.Having established artificial neural network on the basis of finite element data, the interpolation prediction of stress and strain response in the head of solid rocket propellant was made. Artificial neural network output, the maximum Mises stress at the splicing band σ and the maximum Mises strain of the circular arc at top of the stress-releaser ε1and ε2, as target function, the stress-releaser structure of propellant gain was optimized using the genetic algorithm. An optimized design scheme was obtained and good optimization effect was achieved.