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A Numerical Model to Analyze the Transient Behavior and Instabilities on Hybrid Rocket Motors

机译：混合动力火箭发动机瞬态行为和不稳定性的数值模型

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The study of hybrid rocket transient behavior is a very important issue in order to analyze and control instabilities and in the development of throttable devices. In this paper an unsteady numerical model is presented. The model is composed by three sub-model linked together: (ⅰ) zero-dimensional model of the combustion chamber, (ⅱ) 1-D radial model of the fuel grain, (ⅲ) zero dimensional model of the feeding system. The first model simulates combustion chamber dynamic. The 1-D radial model of the fuel grain includes both standard polymeric and liquefying propellants characterized by a melting layer. The fuel block models the heat exchange to the wall, heat propagation through the fuel, and the fuel surface evaporation and entrainment. Finally the feeding-line block simulates the unsteady behavior of the feeding line and droplets break-up and evaporation dynamic. In the following paper all the blocks are presented together with their validation versus analytical test cases and, for each block, with an analysis of the effect of the influencing parameters on the transient thruster behavior.
机译：为了分析和控制不稳定性以及在可节流装置的发展中，混合动力火箭瞬态行为的研究是一个非常重要的问题。本文提出了一个非稳态数值模型。该模型由链接在一起的三个子模型组成：（ⅰ）燃烧室的零维模型，（ⅱ）燃料颗粒的一维径向模型，（ⅲ）进料系统的零维模型。第一个模型模拟燃烧室动态。燃料颗粒的一维径向模型包括以熔融层为特征的标准聚合物和液化推进剂。燃料块模拟了与壁的热交换，热量通过燃料的传播以及燃料表面的蒸发和夹带。最终，进料管线模块模拟了进料管线的不稳定行为，液滴飞散和蒸发动态。在以下论文中，将介绍所有模块以及它们的验证与分析测试用例，并针对每个模块，分析影响参数对瞬态推进器性能的影响。

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