火箭引射模态下一次火箭流量优化方法研究

Optimization method for primary rocket mass flow rate in rocket ejector mode

对火箭基组合循环(RBCC)发动机火箭引射模态下一次火箭流量优化方法开展了研究,并对飞行条件下一次火箭流量的变化规律进行了分析。提出了采用有效比冲作为优化目标的一次火箭流量单目标优化模型;建立了求解与一次火箭流量相匹配的二次燃料流量的比例控制方法;在考虑发动机性能优化与弹道分析耦合作用的基础上,采用试验设计和遗传算法,建立了火箭引射模态下一次火箭流量优化方法。针对空中载机发射的RBCC发动机,开展了火箭引射模态下一次火箭流量优化,并根据弹道分析结果,给出了飞行条件下一次火箭流量变化规律。结果表明,为了克服飞行过程中声障阻力,一次火箭流量在Ma=1.0附近达到最大,此时对发动机提出较高的推力设计要求;在Ma=1.5附近,来流空气的冲压作用占主导地位,一次火箭流量出现较大程度的节流,此时对发动机提出较高的比冲设计要求;超过Ma=1.5后,一次火箭以较小的流量状态维持稳定工作;火箭引射模态下一次火箭流量调节比达到了5.0。

Optimization method of primary rocket mass flow rate was studied for rocket based combined cycle（RBCC） in rocket ejector mode,and the mass flow rate variation investigated along the flight trajectory.An optimization model for primary rocket mass flow rate was proposed by adopting the effective specific impulse as the single optimization objective in rocket ejector mode.The proportion-control method was established for solving secondary fule mass flow rate,which matches the primary rocket mass flow rate.Based on the experiment design and genetic algorithm methodology,optimization method for primary rocket mass flow rate in rocket ejector mode was established in considering the couple relationship between performance optimization and trajectory simulation.Optimization of primary rocket mass flow rate in rocket ejector mode was investigated for air-launching RBCC vehicle to provide the variable mass flow rate in the flight operation.It shows that the primary rocket mass flow rate reaches the peak for overcoming the sound barrier,which brings about much higher design requirement for thrust;The primary rocket mass flow rate begins to throttle for the domination of ram effect over ejection effect,which brings about much higher design requirement for specific impulse;the primary rocket maintains a low level of mass flow rate for stable operation above Ma=1.5.The regulating ratio of primary rocket mass flow rate reaches 5.0 in rocket ejector mode.