火箭冲压组合发动机亚燃模态流道匹配特性分析

Numerical analysis of full flow path in RBCC engine on matching relationship between combustion organization, air intake and exhaust was carried out from Mach number 3 to 6 at ramjet mode to reflect effects of different injection position and equivalence ratio on operating characteristic. With flight Mach number increasing, pressure ratio in the isolator was improved which led main reaction zone moved forward and injection law was adjusted to maximize the function of pre-combustion train. At low Mach flight conditions, main reaction zone need to move backward and broaden high pressure range in the rear part with great expansion to maximize the function of thermal choking. Through heat released in different zones, performance was optimized at a wide range. Besides, closure of rocket moved pre-combustion shock train backwards which improved the condition of inlet and overall impulse performance more than 10%. Meanwhile equivalence ratio should be increased to ensure the overall thrust performance at low Mach flight condition.