一、前言 侵蚀燃烧作为一个对固体火箭发动机设计水平密切相关的重要课题,国内外经30年的努力,至今还没能完全掌握它的细节。代表性的理论是L-R公式和K.K.Kuo的化学反应湍流边界层理论等。为更清楚地了解侵蚀燃烧规律性,本文对燃烧表面附近边界层的气流状态,根据已有理论定量作了分析,并由宏观传热理论导出计算侵蚀燃烧速度的理论显式。 I. Preface Erosion and combustion As an important issue closely related to the design level of solid rocket motors, 30 years of hard work at home and abroad have not yet fully mastered its details. Representative theory is the L-R formula and K.K.Kuo’s chemical reaction theory of turbulent boundary layer. In order to understand the regularity of erosion and combustion more clearly, this paper analyzes the airflow state in the boundary layer near the combustion surface according to the existing theoretical quantitative analysis, and derives the theoretical explicit formula to calculate the erosion and combustion velocity by the macro heat transfer theory.