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本文提出了表征固体推进剂燃速的一种分析方法。它不同于传统的燃速处理方法,用一台发动机点火即可表征推进剂在一定压力范围下的燃速。该方法将修改的弹道试验发动机和一个计算机分析程序包结合起来完成这一任务。本文详细地叙述了所采用的发动机,其药柱通道为锥形,以产生非等面燃烧压力——时间曲线。此外,讨论了计算机分析程序包。这一分析程序包采用一个内弹道模型,用优化方法确定燃速规律。这一分析方法已由一整套理论研究所证实,并提出了这些研究的某些结果。此外,本方法对复合和双基两种推进剂都进行了试验验证。这些试验结果表明,由单个试验发动机点火试验处理的燃速数据和常规方法处理的数据符合较好。本文也给出了这些研究的某些结果。
In this paper, an analytical method to characterize the burning rate of solid propellant is proposed. It is different from the traditional burning rate method, with a single engine ignition can be characterized by the propellant in a certain pressure range of burning rate. The method accomplishes this by combining the modified ballistic test engine with a computer analysis package. This article describes in detail the engine used, with its passageway tapered to create a non-isometric combustion pressure vs. time curve. In addition, the computer analysis package is discussed. This analysis package uses an internal ballistic model to determine the combustion rate law using an optimization method. This method of analysis has been corroborated by a whole set of theoretical studies and presented some of the results of these studies. In addition, both the composite and bi-based propellants were tested by this method. The results of these tests show that the burn rate data processed by a single test engine ignition test is in good agreement with the data processed by conventional methods. This article also gives some of the results of these studies.