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提出了予示固体推进剂火箭发动机的比冲和特性速度的分析方法。这个方法强调了二维两相流分析,它是以准确的跨音速解为基础,并且给出金属含量高的推进剂的大部分性能损失。它应用于可忽略燃烧损失和出口锥上无粒子撞击的发动机。以一系列的缩比发动机、全尺寸发动机和5台装有高膨胀比喷管的远地点发动机实验结果为背景,评价了它的有效性。膨胀比在很宽的范围内(从9到92)在予示值和实验结果之间完全一致。从本研究得出结论,提出的这个方法是性能予示的一个很准确工具,并且对高膨胀比喷管的气动力设计和分析很有用,这样的喷管对期待中的未来应用是特别有意义的。
Proposed to show solid propellant rocket engine specific impulse and characteristic velocity analysis. This method emphasizes two-dimensional two-phase flow analysis, which is based on accurate transonic solutions and gives most of the performance loss of a metal-rich propellant. It applies to negligible combustion losses and exit cone without particle impact on the engine. Its effectiveness was evaluated on the basis of experimental results of a series of engine reductions, full-size engines and five apogee engines equipped with high expansion ratio nozzles. The swell ratio is very broad (from 9 to 92) and is exactly the same between the pre-indicated values and experimental results. From this study it is concluded that the proposed method is a very accurate tool for performance and is useful for aerodynamic design and analysis of high expansion ratio nozzles that are particularly desirable for future applications meaningful.