摘要
发展了燃烧室的分区模型 :将燃烧室分为两个区 ,一个是燃烧区 ,采用时滞燃烧瞬时均匀混合模型 ,另一个是流动区 ,连同喷管一起 ,采用一维理想气体流动的有限元状态变量模型。给出了一个利用该模型计算发动机起动过程的一个算例 ,计算结果表明该模型可较好地描述液体火箭发动机燃烧室的建压及非稳态流动过程。模型采用状态方程形式 ,具有形式简单、计算简便的特点 。
An innovative partition model of liquid rocket engine combustion chambers is developed in this paper,which divides combustion chambers into two regions.One region is named as combustion region in which propellant changes into combustion gas instantaneously after constant time lag,and the combustion gas instantaneously and uniformly mixes with the staying gas of the region.The other is flow region,in connection with nozzle being treated as ideal gas pipe and being modeled by employing the finite element state variable model of one dimensional ideal gas flow.An example using the model to calculate the start up process of a liquid rocket engine is given,and the calculated results show that the model describes the thrusters' transients well.The model is expressed in the form of state variable equations,therefore it has simple expressions and can be solved easily.It is suitable for the simulation and control of liquid rocket engines.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2002年第1期135-139,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)
关键词
液体火箭发动机
燃烧室
分区模型
有限元
状态变量模型
liquid propellant rocket engines
combustion chambers
partition model
finite elements
state variable model
