火箭基组合循环(RBCC)推进系统概念设计模型  

Conceptual design model of rocket base combined cycle propulsion system

作　　者：黄生洪[1] 何洪庆[1] 何国强[1] 刘佩进[1] 秦飞[1] 王国辉[1] 

机构地区：[1]西北工业大学航天工程学院,陕西西安710072

出　　处：《推进技术》2003年第1期1-5,共5页Journal of Propulsion Technology

基　　金：国防科技重点实验室基金试点项目 (0 0JS60 3 3ZK0 4 0 1)

摘　　要：简述了火箭基组合循环 (RBCC)推进系统及相应概念设计模型的发展与不足 ,并应用准一维流动理论及化学反应动力学理论建立了RBCC一维性能预估数学模型。该模型耦合了有限化学反应速率模型 ,考虑了包括变几何截面积、引射流动、燃料喷注、混合、燃烧及摩擦损失等多种影响流动的因素 ,并采用变步长半隐式多步龙格 库塔方法进行了数值求解。The Rocket-Based-Combined-Cyele Propulsion system and the development of it's conceptual design model were briefly described. Based on the analysis of current model's shortcomings, an one-dimensional performance computation model was established by applying quasi-one-dimensional flow model and chemistry model. In this model, multiple elements, such as variable cross section area, ejecting, fuel injecting, mixing, combustion and so on were considered. The model was solved by implicit RK algorithm, the results agree with the literature.

关 键 词：推进系统 概念设计 火箭发动机 引射式冲击发动机 复合式发动机 性能预测 概念模型 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]