基于能量法的超声速飞航导弹／冲压发动机一体化研究  

Research of supersonic cruise missile and ramjet motor integration based on energy method

作　　者：陈玉春[1] 崔高锋[1] 杨云铠[1] 黄兴[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《固体火箭技术》2009年第2期119-122,130,共5页Journal of Solid Rocket Technology

摘　　要：参考飞机/发动机一体化设计的思路,建立了基于能量法的超声速飞航导弹/冲压发动机一体化设计的约束分析和任务分析模型。简述了超声速飞航导弹任务剖面、约束条件的给定、导弹的质量组成以及冲压发动机安装模型。利用高超声速飞行器的升阻特性,对超声速飞航导弹的升阻特性进行了预测。分析了冲压发动机性能、导弹升阻比对导弹发射总重的影响。约束分析和任务分析的计算结果表明,所建立的一体化约束分析与任务分析模型是合理可行的。Referring to the analysis method of aircraft and engine integration, a model based on energy method of supersonic cruise missile and ramjet motor integration constrain analysis and mission analysis was developed. The mission, constrain conditions, and mass composition of the missile and the installation model of ramjet motor were presented. A prediction method of liftdrag ratio of supersonic maneuverable missile was given. The influences of ramjet motor performance and lift-drag ratio on missile launch weight were analyzed. The constrain-analysis results and the mission-analysis results indicate that the model of integration constrains analysis and mission analysis is reasonable and feasible.

关 键 词：超声速飞航导弹 冲压发动机 一体化研究 约束分析 任务分析 

分 类 号：V435.1[航空宇航科学与技术—航空宇航推进理论与工程]