关键词: 固体火箭超燃冲压发动机, 硼颗粒, 正交设计, 交互作用, 燃烧效率

Abstract: To study the ignition and combustion characteristics of boron particles in a solid rocket scramjet engine and the impact of the combustor structure on engine combustion performance, a User-Defined Function program characterizing the ignition and combustion processes of boron particles was developed. This study analyzed the dynamic characteristics of condensed-phase particle combustion energy release in ramjets. Furthermore, based on the orthogonal design experimental method, the study analyzed the effects of boron particle size, gas injection angle, and cavity depth, as well as their interactions, on engine combustion efficiency from the perspectives of particle characteristics and engine structure. Through range and variance analyses, the factors influencing engine combustion efficiency were ranked as follows: boron particle size > interaction between particle size and gas injection angle > gas injection angle > cavity depth > interaction between gas injection angle and cavity depth > interaction between particle size and cavity depth. The optimal combination achieved a combustion efficiency of 77.01%. The results indicate that boron particle size significantly affects the combustion efficiency of the solid rocket scramjet engine, and the interaction between particle size and gas injection angle cannot be ignored.

Key words: solid rocket scramjet engine, boron particles, orthogonal design, interaction, combustion efficiency