基于Rao方法的二维单壁膨胀喷管优化设计

推进技术 ›› 2009, Vol. 30 ›› Issue (4): 451-456.

基于Rao方法的二维单壁膨胀喷管优化设计

周正,倪鸿礼,贺旭照,乐嘉陵

中国空气动力研究与发展中心;中国空气动力研究与发展中心;中国空气动力研究与发展中心;中国空气动力研究与发展中心

发布日期:2021-08-15
基金资助:
国家“八六三”高超声速技术研究基金(2006AA723041)

Optimization design of single expansion ramp nozzle based on Rao’s method

China Aerodynamics Research and Development Center,Mianyang 621000,China;China Aerodynamics Research and Development Center,Mianyang 621000,China;China Aerodynamics Research and Development Center,Mianyang 621000,China;China Aerodynamics Research and Development Center,Mianyang 621000,China

Published:2021-08-15

摘要/Abstract

摘要： 针对高超声速飞行器后体尾喷管的优化设计问题,发展了与多目标优化程序NSGA-Ⅱ相结合的自动优化流程。利用Rao喷管的近似方法建立喷管优化模型,采用区域推进求解PNS方程的流场解算器和网格自动化生成技术获得尾喷管的性能;引入目标约束设计和自适交叉技术,自动加速目标空间的搜索,大幅度提高了多目标优化设计效率;获得了给定来流和喷流条件下的一种具有良好性能的二维后体尾喷管设计方案。

关键词: 高超声速飞行器;航空发动机;一体化设计;喷管;最优设计

Abstract: A multi-objective design optimization circle which has the ability to design a 2-D afterbody/nozzle for air-breathing hypersonic vehicles was presented.A new mathematical nozzle model was proposed by introducing the approach of Rao’s nozzle.In order to obtain the aerodynamic performances of the nozzle,the technologies of automated grid generation and numerical analysis based on region marching PNS equations Solver was introduced.The auto-accelerating ability of searching in objective space was achieved by the technologies of objective constraint and self-adaptive SBX operation.The design technologies mentioned above were implemented to the case of one hypersonic afterbody/nozzle design in given flight condition,and a new scheme with better performance was captured.

Key words: Hypersonic vehicle;Aircraft engine;Integrated design;Nozzle;Optimum design

周正,倪鸿礼,贺旭照,乐嘉陵. 基于Rao方法的二维单壁膨胀喷管优化设计[J]. 推进技术, 2009, 30(4): 451-456.