基于正交试验的固体火箭超燃冲压发动机优化设计

The effects of the ignition and combustion characteristics of boron particles in a solid rocket scramjet engine and the combustor structure on the combustion performance of engine are studied. A user-defined function program for characterizing the ignition and combustion processes of boron particles is written,and the dynamic characteristics of combustion energy release of condensed-phase particles in a ramjet is analyzed. Furthermore,based on the orthogonal design experimental method,the effects of boron particle size, gas injection angle and cavity depth, as well as their interactions on engine combustion efficiency are analyzed from the perspectives of particle characteristics and engine structure. Through range and variance analyses, the results indicate that the factors influencing the engine combustion efficiency are 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 achieves a combustion efficiency of 77. 01%. The boron particle size has a significant effect on the combustion efficiency of solid rocket scramjet engine, and the interaction between particle size and gas injection angle cannot be ignored.