Radiative heat transfer in participating media has a significant impact on the internal thermal environment in solid rocket motor(SRM)with metallized solid propellants.The establishment of accurate and efficient prediction method of participating medium radiation characteristics is an important prerequisite for precise numerical prediction of internal thermal environment in the motor.In this paper,a precise calculation method for the radiative properties of molten alumina particles and multi-component com-bustion gas in the SRM was established based on Mie theory and line-by-line calculation method,respectively.With this method,a fast prediction method for the radiative properties of combustion products in SRM by combining data interpolation method and Planck-mean absorption coefficient global model was constructed.The one-dimensional distribution of radiative parameters of com-bustion products inside the HIPPO nozzle was calculated,and the effects of temperature,pressure of chamber and aluminum content of propellant on the radiative characteristics of combustion products in nozzles were studied.The results show that the contribution of particles to the absorption coefficient of combustion products is dominant between the chamber and the nozzle throat,while the con-tribution of combustion gas can be neglected;in the divergent section of nozzle,the contribution of combustion gas to the absorption coefficient is gradually significant;at the nozzle exit,the contribution of combustion gas to the absorption coefficient is not negligible;the increase of chamber temperature and aluminum content of propellant,and the decrease of the chamber pressure will lead to the decrease of the contribution ratio of gas to radiative heat transfer.
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