SMC燃烧模式下引射火箭性能影响因素的实验研究

Experimental study for factors affecting rocket ejector performance in SMC combustion mode

采用富燃的气氧/酒精燃气发生器以及可变结构的引射器后体,研究了引射器后体结构以及一次火箭工作压强对于SMC燃烧模式下引射火箭性能的影响。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。通过优化引射器后体结构,在SMC二级燃烧模式下工作的引射火箭可以产生较大的推力增强。

Fuel rich gas oxygen/alcohol gas generator and geometry adjustable ejector combustor were employed to investigate the effect of ejector combustor geometry and primary rocket chamber pressure on ejector rocket performance in SMC combustion mode. 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. By optimizing ejector eombustor geometry, ejector rocket in SMC combustion mode can obtain comparable thrust augmentation.