Solid rocket engine tail flame radiation computational grid optimization method and device

The invention relates to the technical field of infrared imaging, in particular to a solid rocket engine tail flame radiation computational grid optimization method and device. The method comprises the following steps: reading the number of grid points, the number of grid surfaces and the number of variables in a grid file; the grid file is obtained by performing flow field calculation on the tail flame of the solid engine by utilizing flow field calculation software, and the grid file comprises internal flow field data and external flow field data; determining the number of axial grids and the number of radial grids in an external flow field by taking a nozzle outlet of the solid rocket engine as an interface of the internal flow field and the external flow field; rearranging the grid points in the external flow field based on the number of the axial grids and the number of the radial grids to obtain a structured external flow field grid; and a preset strategy is adopted to encrypt the external flow field gr