吸气式高超声速飞行器三维后体尾喷管优化设计

推进技术 ›› 2009, Vol. 30 ›› Issue (6): 687-690.

吸气式高超声速飞行器三维后体尾喷管优化设计

贺旭照,倪鸿礼,周正,乐嘉陵,宋文艳

西北工业大学动力与能源学院;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;西北工业大学动力与能源学院

发布日期:2021-08-15
基金资助:
国家“八六三”基金项目(2006AA723041)

3D afterbody nozzle optimization of air-breathing hypersonic vehicle

School of Power and Energy, Northwestern Polytechnical Univ., Xi’an 710072, 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 621001, China;China Aerodynamics Research and Development Center, Mianyang 621002, China;School of Power and Energy, Northwestern Polytechnical Univ., Xi’an 710072, China

Published:2021-08-15

摘要/Abstract

摘要： 三维后体尾喷管是吸气式高超声速飞行器产生推力、升力的关键部件,需要精细设计,最大限度地提升三维膨胀过程中的气动特性。本文在二维后体尾喷管优化设计的基础上,发展了一种三维后体尾喷管的优化设计方法。通过参数化建模、三维喷管计算网格自动生成、空间推进CFD解算器及NSGA-II多目标优化软件等技术手段,对后体尾喷管三维构型进行了多目标优化设计。优化后的三维后体尾喷管与原始喷管相比,推力和升力都得到了较大提升。

关键词: 高超声速飞行器;三维后体尾喷管;多目标优化;空间推进算法

Abstract: 3D after-body nozzle of air-breathing hypersonic vehicle is a main part for generating thrust and lift. It needs careful design to maximum aerodynamic expansion characteristic. Based on 2D after-body nozzle optimization method, a 3D after-body nozzle optimization method is developed. Combining parameterized shape generating, 3D nozzle computation grid auto-generation, matured 3D space-marching CFD solver and NSGAII multi-objects optimization techniques, 3D nozzle configuration is optimized in multi-objective way. The nozzle thrust and lift have been improved after optimization.

Key words: Hypersonic vehicle;3D after-body nozzle;Multi-objects optimization;Space marching algorithm

贺旭照,倪鸿礼,周正,乐嘉陵,宋文艳. 吸气式高超声速飞行器三维后体尾喷管优化设计[J]. 推进技术, 2009, 30(6): 687-690.