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《Journal of Astronautics》 1988-04
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Zhao Yin Tian Deyu Jiang Yu(National University of Defense Technology)  
A comprehensive model describing the combustion of composite solid propellants has been developed in this paper. This model discusses in more detail the condensed-phase reactions, emphasizes the importance of the heat transfer in all forms on the burning surface and proposes that the linear combustion rate of propellant should be expressed by the Linear decomposition rate of the inert binder. A Large number of concrete calculations have also been made and compared to the experimental data. For the AP/HTPB propellants, the calculated results of which the relative error is Less than 10% make up 80% and for the AL/AP/HTPB, make up more than 90%.
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