Modeling of Hybrid Rocket Low Frequency Instabilities
Modeling of Hybrid Rocket Low Frequency Instabilities
复制标题
混合火箭低频不稳定性建模
DOI：
10.2514/1.7792
复制
发表时间：
2005
影响因子：
1.9
通讯作者：
G. Zilliac
中科院分区：
文献类型：
--
作者：
M. Karabeyoğlu;S. D. Zilwa;B. Cantwell;G. Zilliac
混合火箭的综合动态模型已经开发出来，用于理解和预测包括不稳定性在内的瞬态行为。瞬态模型的线性化版本预测了混合动力中常见的低频腔室压力振荡。不稳定性的根源在于固体燃料中的热瞬变、由于燃料回归速率引起的壁传热阻塞以及燃料表面上形成的边界层中的瞬变的复杂耦合。线性化理论预测的振荡频率与混合动力推进文献中获得的 43 个电机测试结果非常吻合。比较中使用的电机测试数据涵盖了非常广泛的参数，包括1）四个独立的研发项目； 2）三种不同的氧化剂（液氧、气态氧和一氧化二氮）； 3) 多种电机尺寸，即从 5 英寸（12.7 厘米）直径到 72 英寸（182.9 厘米）直径，以及运行条件； 4) 几种燃料配方。还建议了主振荡模式频率的简单通用缩放公式。
A comprehensive dynamic model of a hybrid rocket has been developed to understand and predict the transient behavior including instabilities. A linearized version of the transient model predicted the low-frequency chamber pressure oscillations that are commonly observed in hybrids. The source of the instabilities is based on a complex coupling of thermal transients in the solid fuel, the wall heat transfer blocking due to fuel regression rate, and the transients in the boundary layer that forms on the fuel surface. The oscillation frequencies predicted by the linearized theory are in very good agreement with 43 motor test results obtained from the hybrid propulsion literature. The motor test data used in the comparison cover a very wide spectrum of parameters including 1) four separate research and development programs; 2) three different oxidizers (liquid oxygen, gaseous oxygen, and nitrous oxide); 3) a wide range of motor dimensions, that is, from 5 in. (12.7 cm) diameter to 72 in. (182.9 cm) diameter, and operating conditions; and 4) several fuel formulations. A simple universal scaling formula for the frequency of the primary oscillation mode is also suggested.