The results show that ejector combustor geometry is the key factor to ejector rocket relative thrust in SMC combustion mode, and primary rocket chamber pressure plays a subordination role.

• 实验结果表明，引射器后体结构对于提高SMC二级燃烧模式下引射火箭的相对推力非常关键，而一次火箭工作压强的作用相对较小。