Numerical Calculation And Research Of Thermal Environment For Projectiles' Head With Heat Source Term

In the unstructured meshes, the diffusion equations were solved by using the finite volume method (FVM). The unsteady state term was discretized using the full implicitly schemes. For the diffusion terms, the normal direction vector (the first diffusion) and the tangent direction vector (the second diffusion) were calculated by using the intersectant and iterative algorithm. The 2D and 3D programs have been created by Fortran77/90/95, and the pre-processor has been connected with the commercial software such as Tecplot and Gambit.The thermal neutron flux and the heat generation distributions of the nuclear power reactors with reflected layer were computed. There are two kinds of situations in the heat generation distribute, the one is a function of location space (Bessel function distribution is used to the radial direction and Cosine function distribution is used to the axis direction); the other is dependent on temperature (the systems have negative or positive reactivity); and then the temperature fields were obtained. The results indicate that the reflector can heighten the power of the nuclear reactor.The engineering methods were applied in the calculation for the heat flux of the stagnation, and the hemisphere and cone-shaped body, for the hypersonic aerodynamic heating of the ballistics missile head. These heat fluxes were linearizated as the third kind of boundary conditions and coupled with the numerical calculation in the missile body. The different circular radius of the nuclear battle disposition was located in the missile head, and the heat source ratio with the Sinned function distribution at radial direction was provided. The temperature fields of the projectile's head were simulated, and the high temperature distribution and the dynamic temperature field have been gained.The results indicate that the tiptop temperature's area of the projectile's head aggrandize when the radius of the source terms increase. The heat generation and the aerodynamic heating are important factors of the head's temperature field. The results can provide useful reference for the design of the heat shield and the optimization of missile head.