论文部分内容阅读
火箭基组合循环(RBCC)推进系统在引射模态时存在火箭发动机和冲压发动机的共同工作,为了分析引射模态时进气道的性能和流场特征,根据RBCC的特点,设计了一种RBCC用二元式进气道,采用数值模拟方法研究了不同飞行高度、马赫数和掺混段反压下火箭射流对进气道性能的影响。研究发现,火箭发动机的工作状态决定了火箭射流对进气道性能的影响:当火箭发动机工作在过膨胀状态时,火箭射流的引射抽吸作用明显提高了推进系统的抗反压能力,但并不改善进气道的起动能力;当火箭发动机工作在欠膨胀状态时,火箭射流的压力扰动会使进气道扩压段产生结尾激波,进气道性能随之改变。
In order to analyze the performance and flow field characteristics of the inlet duct in the injection mode, a RBCC propulsion system is proposed to work together with a ramjet and a ramjet engine in the injection mode. According to the characteristics of the RBCC, The RBCC uses a binary inlet to simulate the effects of rocket jets on the performance of the air intake at different flight levels, Mach number and back pressure in the mixed section. The research shows that the working status of rocket engine determines the influence of rocket jet on the performance of air intake: when the rocket engine works in over-inflated state, the jet suction of rocket jet enhances the anti-back pressure capability of propulsion system obviously, And does not improve the starting ability of the air intake. When the rocket engine works in an under-expanded state, the pressure disturbance of the rocket jet will cause an end shock wave in the diffuser section of the air intake, and the performance of the air intake channel changes accordingly.