涡流混气中冷等离子体点火特性研究

To ensure the safe operation of the ramjet under large angles of attack and significant sideslip， and to address the issue of the ramjet engine stalling during missile maneuvering， a low-temperature plasma igniter that shares the gas source and fuel with the ramjet engine was designed. This study focused on plasma ignition within the vortex mixture of the ramjet engine under different incoming flow conditions. The research included an analysis of the ignition characteristics of low-temperature plasma in the vortex mixture of the ramjet engine. By examining the flow field of the ignition combustion chamber， the optimal installation position and operating state of the igniter were determined based on the low-speed regions of the ramjet mixture. Single-phase ignition experiments were conducted to study the effects of different ignition structure sizes on the length and intensity of the combustion flame. Joint experiments of the igniter and engine were performed to analyze the ignition characteristics of the engine based on the plasma igniter. The results indicate that the low-temperature plasma igniter effectively meets the requirements for multiple ignitions and continuous combustion of the ramjet. The igniter exhibited good combustion performance under different air speeds， temperatures and fuel conditions.