基于分布参数线性化模型的分级燃烧循环液体火箭发动机频率特性计算  

Frequency Characteristics Computation of Liquid Rocket Engine Based on Distributed Parameter Models

作　　者：陈琪锋[1] 刘昆[1] 张育林[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《航空动力学报》2001年第1期44-48,共5页Journal of Aerospace Power

基　　金：国家自然科学基金资助项目! (5 98860 0 3 )

摘　　要：采用一维分布参数模型描述发动机的管路系统 ,将发动机各部件和管路的线性化模型表示为联系输入输出参数的传输矩阵形式。根据发动机各部件的连接关系 ,将发动机系统划分为若干模块 ,用矩阵变换的方法求得发动机各模块的传输矩阵 ,构成发动机系统方程组 ,用数值求解的方法计算了某分级燃烧循环液氧Linearized distributed parameter models are used to compute frequency responses of liquid rocket engine.One-dimensional distributed parameter models are used to describe engine pipelines.Other engine components are described in lumped parameter models.The linearized models of engine pipelines and components are transformed to frequency domains.Engine elements frequency domain models are described as transmission matrixes,which relates input and output variables of the engine elements.Engine system is divided into several modules according to the connections between engine elements.Matrix transform methods are used to obtain module transmission matrixes from element transmission matrixes.Equations of engine system are constituted from module transmission matrixes.These equations relate system variables and disturbances.It is convenient to generate different rocket engine systems and compute their frequency characteristics according to their own structure and parameters.The frequency characteristics of a staged combustion cycle LOX/LH2 liquid rocket engine have been analyzed numerically.

关 键 词：液体推进剂火箭发动机 分级燃烧循环 频率特性 分布参数线性化模型 

分 类 号：V434.1[航空宇航科学与技术—航空宇航推进理论与工程]