液体冲压发动机燃油充填过程仿真研究  

Transient simulation of liquid fuel filling process of ramjet

作　　者：吴宝元[1] 王玉峰[1] 胡宝文[2] 

机构地区：[1]西安航天动力研究所,陕西西安710100 [2]西北工业大学航天学院,陕西西安710072

出　　处：《火箭推进》2016年第5期1-5,共5页Journal of Rocket Propulsion

基　　金：国家863项目(2012AA7053021)

摘　　要：为了研究液体冲压发动机在起动期间燃油的动态充填过程,利用AMESim仿真软件对冲压发动机燃油调节控制系统进行了建模仿真。建立了空气涡轮、离心泵、燃油调节器、燃油控制器、膜片阀及充填管路的仿真模型。基于该模型对冲压发动机点火起动时的燃油充填过程进行了仿真计算,分析了不同膜片阀破裂散差情况下冲压发动机充填过程的差异。结果表明,在给定涡轮入口压力条件下,当燃烧室各供油路膜片阀破裂散差过大时,会造成破裂压差大的膜片阀所在的管路无法实现可靠充填,从而影响发动机的点火起动过程和正常工作。Dynamic modeling and simulation of the fuel supply and control system in liquid fueled ramjet was conducted with AMESim to study the dynamic fuel filling process of the ramjet in its working state. The simulation .models of air turbo, centrifugal pump, fuel regulator, fuel controller, membrane valve and fuel filling pipe were established. The fuel filling process of the ramjet at the time of its ignition startup was simulated and calculated on the basis of these models. The difference of the fuel filling process of the ramjet in the case of broken scattering difference of the different membrane valves is analyzed. The results show that, with same inlet pressure of air turbo, the pipe with the membrane valve working at large rupture pressure can not achieve the reliable fuel filling, which may affect the ignition startup and regular work of the ramjet .

关 键 词：亚燃冲压发动机 燃油调节系统 膜片阀 燃油充填过程 AMESIM 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]