论文部分内容阅读
在地面 M=2模拟飞行条件下,对整体助推器的火箭-冲压发动机的简单的独创方案作了试验鉴定。这种被称为“空气动力”的方案采用双重功能的喷管,既用于加速也用于巡航飞行,完全用固体燃料,且没有任何要分离的活动部件。就结构紧凑而言,这种方案与那种把助推器完全包容在冲压发动机燃烧室里的完全整体的方案(所谓“机械”方案)比较起来略为逊色,但从技术工艺上讲却简单得多。由于在巡航飞行时采用自动热分解大比重固体燃料,使本发动机有可能在一方面,具有比采用煤油时更高的单位容积冲量(单位燃料容积的比冲);另一方面,其简易程度又可与固体火箭相比拟。大比例尺模型上的综合试验证实了分析结果,特别证实了关于环形双重功能的尾喷管以及固体燃料燃烧室的分析。试验还表明,将这一台发动机用于两个飞行阶段上的巨大灵活性。看来,这种发动机的性能可能适用于某些战术性军事用途。
The simple, original scheme of the rocket-ramjet engine for the overall booster was tested on ground M = 2 simulated flight conditions. This so-called “aerodynamic” solution features a dual-function nozzle that is used both for acceleration and cruise flight, complete with solid fuel and without any moving parts to be separated. In terms of compactness, this solution is somewhat inferior to a completely integral solution (the so-called “mechanical” solution) that completely embraces the booster in the ramjet’s combustion chamber, but is technically very simple many. Due to the automatic thermal decomposition of large specific gravity solid fuels during cruise flight, it is possible for the engine to have, on the one hand, a higher unit volume impulse (specific impulse per unit fuel volume) than with kerosene; on the other hand, its ease Can be compared with the solid rocket. Comprehensive tests on large-scale models confirm the results of the analysis, in particular, confirming the analysis of the annular dual-function tailpipe and the solid fuel combustor. The tests also showed that this engine was used for great flexibility in two phases of flight. It appears that the performance of this engine may be suitable for some tactical military purposes.