线性可调汽蚀文氏管设计与数值仿真研究  

On Design and Numerical Simulation for Linear Throttling Cavitation Venturi

作　　者：唐飞[1] 李永[1] 耿永兵[1] 李文[1] 林长杰[1] 

机构地区：[1]北京控制工程研究所,北京100190

出　　处：《空间控制技术与应用》2013年第6期12-16,22,共6页Aerospace Control and Application

基　　金：国家高技术研究发展计划(863)资助项目(2011AA8015025C)

摘　　要：可调汽蚀文氏管是变推力火箭发动机实现推进剂流量和推力大范围调节的关键部件.在设计线性可调汽蚀文氏管模型的基础上,采用基于Rayleigh-Plesset方程的混合流体模型,进行了相关的数值分析.计算结果表明:设计的线性可调汽蚀文氏管可以实现流量的大范围调节,并且流量与调节锥行程呈线性变化关系,满足设计要求.Throttling cavitation venturi, which can control the propellant flux and thrust in a wide range, is an important component of throttling rocket engine. Based on the designed model, a numerical simula tion of cavitation flow in venturi is performed with a mixture model based on RayleighPlesset equation. The results indicate that the linear throttling cavitation venturi can regulate the propellant flux in a wide range. Furthermore, the flux changes linearly with respect to the movement of actuator. The proposed cavitation venturi can satisfy the need of design.

关 键 词：可调汽蚀文氏管 变推力火箭发动机 混合比调节 推进剂流量调节 

分 类 号：V432[航空宇航科学与技术—航空宇航推进理论与工程]