双调变推力液体火箭发动机的喷注器结构对燃烧效率及稳定性之影响

On the Effects of Injector Struction of Double-adjustable Liquid Rocket Engine upon It′s Combustion Effenciency and Stablity

针对双调变推力液体火箭发动机研制过程中所使用过的二种不同结构的喷注器 ,在实验的基础上 ,定性地分析了它们对燃烧效率 φc 及稳定性的影响 ,并就双调发动机研制过程中出现的燃烧效率过高及燃烧不稳定现象作了初步探讨。

In this paper propulsive effects upon the combustion effenciency and stability of two dissimilar-constructed injectors,applied in the edvelopment process of double-adjustable liquid rocket,are qualitatively analyzed, moreover, a preliminary research on the execssive combustion effenciency and instablity is made.