超燃冲压发动机一体化设计与优化方法研究  

Integrated design and optimization method for scramjet

作　　者：徐大军[1] 孙冰[1] 徐旭[1] 王元光[1] 陈兵[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《推进技术》2002年第5期360-362,共3页Journal of Propulsion Technology

基　　金：国家"八六三"基金资助项目(863 2 1 4 10)。

摘　　要：建立了超燃冲压发动机一体化设计的优化模型,研究了超燃冲压发动机在总体性能要求与约束条件下,进气道、燃烧室(含隔离段)、尾喷管之间的性能匹配和参数优化。针对将计算流体力学(CFD)方法应用到优化设计过程中所带来的运算量巨大的问题,引入了基于PVM(并行虚拟机)的遗传算法,为包含有复杂流场计算过程的优化设计问题提出了一条易于实现并经济、可靠的解决途径。An optimization model was established for integrated scramjet design. Under the condition of integrated design requirement, performance mach and parameters optimization of the inlet/combustor/nozzle were researched. Genetic Algorithms (GA) based on parallel virtual machine (PVM) was introduced to reduce the large calculation when using CFD methods in the optimization design. An operational, economical and reliable method was developed to resolve the optimization design including complex flowfield calculation.

关 键 词：优化 超音速燃烧 冲压喷气发动机 一体化设计 数值仿真 

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]