一体化超燃冲压发动机初步设计计算模型  

Primary calculating model for integrated scramjet engine design

作　　者：张蒙正[1] 张忠利[1] 葛李虎[1] 仲伟聪[1] 

机构地区：[1]陕西动力机械设计研究所,陕西西安710100

出　　处：《火箭推进》2005年第1期14-20,共7页Journal of Rocket Propulsion

摘　　要：以总压恢复系数最大为目标,采用等激波强度和等激波角设计方法建立进气道模型;采用Ikawa“面积扩张因子”建立燃烧室模型;依据Edward方法初估尾喷管型面。在此基础上建立了一体化超燃冲压发动机进气道、隔离段、燃烧室及尾喷管计算模型,并对一体化设计的超燃冲压发动机模型进行了初步计算。The inlet design calculating model was set up based on the theory of equal shock wave intensity and angle of supersonic airflow to get maximum total pressure coefficient. The calculating model of combustion chamber performance was built by using the method of Ikawa, and nozzle contour was obtained by Edward’s method. Based on these efforts, primary calculating models for integrated scramjet engine inlet, separating section, combustion chamber and nozzle were built, and the primarily calculations were conducted.

关 键 词：超燃冲压发动机 计算模型 设计方法 进气道 燃烧室 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]