大推力氢氧发动机的频率特性仿真研究  

Research on frequency characteristics of LOX/LH_2 rocket engine

作　　者：王珏[1,2] 张振鹏[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191 [2]中国运载火箭技术研究院,北京100076

出　　处：《航空动力学报》2008年第12期2341-2345,共5页Journal of Aerospace Power

摘　　要：采用传递矩阵法对某大推力氢氧火箭发动机系统的频率特性进行了仿真分析.首先建立发动机系统管路和部组件的频域线性化数学模型,并根据系统管路和部件的联接关系,简化系统模型,构成了联系扰动量和系统变量的线性方程组,进一步求解得到扰动量作用下系统变量的频率响应特性.通过仿真对比发现燃气发生器循环与分级燃烧循环的氢氧火箭发动机系统频率特性有显著差异.The frequency characteristics of a gas generator cycle liquid oxygen / liquid hydrogen （LOX/LH2） rocket engine system was analyzed numerically using matrix transform method. One-dimensional distributed parameter models were used to describe the pipelines and other components of the engine system. The models were transformed to frequency domains and described as transmission matrixes. According to the connecting relationship of the engine elements, the engine system was divided into several modules with corresponding transmission matrixes. The linear equations of engine system, which relate system variables and perturbations, were constituted from module transmission matrixes. The frequency characteristics of the system variables were thus obtained from these equations. For the purpose of validation, the frequency characteristics of a staged combustion cycle LOX/LH2 rocket engine system was analyzed as well to show the difference with the one of the gas generator cycle liquid rocket engine system.

关 键 词：氢氧发动机 频率特性 燃气发生器循环 分级燃烧循环 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]