超声速飞行器声爆/气动力综合设计技术研究

刘刚; 黄江涛; 周铸; 陈作斌; 高正红; 钟世东; 肖涵山

doi:10.7638/kqdlxxb-2020.0051

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超声速飞行器声爆/气动力综合设计技术研究

研究论文 | 更新时间：2026-05-28

- 超声速飞行器声爆/气动力综合设计技术研究
- Investigation of supersonic low sonic boom aerodynamic configuration design
- 空气动力学学报 2020年38卷第5期页码：858-865
- 作者机构：
  
  1. 中国空气动力研究与发展中心,绵阳,621000
  2. 西北工业大学航空学院,西安,710072
- 作者简介：
  
  刘刚(1964-), 男, 研究员, 研究方向:飞行器气动设计、计算流体力学.E-mail:liugangdy@sina.com
  黄江涛(1982-), 男, 副研究员, 研究方向:飞行器气动设计与多学科优化、计算空气动力学.E-mail:hjtcyf@163.com
- 基金信息：
  
  基础与前沿技术基金重点项目（PJD20190095）;装备预先研究项目（41406030301）
- DOI：10.7638/kqdlxxb-2020.0051
  中图分类号： V211.3
- 纸质出版：2020
- 稿件说明：
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刘刚, 黄江涛, 周铸, 陈作斌, 高正红, 钟世东, 肖涵山. 超声速飞行器声爆/气动力综合设计技术研究[J]. 空气动力学学报, 2020, 38(5): 858-865.

LIU Gang, HUANG Jiangtao, ZHOU Zhu, et al. Investigation of supersonic low sonic boom aerodynamic configuration design[J]. 2020, 38(5): 858-865.
刘刚, 黄江涛, 周铸, 陈作斌, 高正红, 钟世东, 肖涵山. 超声速飞行器声爆/气动力综合设计技术研究[J]. 空气动力学学报, 2020, 38(5): 858-865. DOI： 10.7638/kqdlxxb-2020.0051.

LIU Gang, HUANG Jiangtao, ZHOU Zhu, et al. Investigation of supersonic low sonic boom aerodynamic configuration design[J]. 2020, 38(5): 858-865. DOI： 10.7638/kqdlxxb-2020.0051.

摘要

低声爆气动外形设计是超声速民机研发的一项关键技术。基于笛卡尔无黏求解器进行了典型民机构型的低声爆设计选型，主要研究了机身轴线弯曲度、机翼平面形状、机身截面积特征等因素对近场过压分布的影响，最终选型出一种超声速飞机气动布局。在此气动布局基础之上，结合自主研发的流场/声爆耦合伴随优化设计软件AMDEsign，在指定的低噪声水平声爆信号的条件下，通过对远场声爆信号进行高效反设计，实现了超声速低声爆气动外形的大规模设计变量数值优化，感觉噪声级大幅度降低，分析了外形变化对声爆抑制作用以及近场波系形态，同时也验证了综合设计技术的有效性。

Abstract

The aerodynamic configuration design of low sonic boom is a key technology in the research and development of supersonic civil aircraft. Based on Cartesian inviscid solver

the design and selection of typical civil aircraft configuration for low boom are carried out. The influence of the curvature of fuselage axis

the plane shape of wing on the distribution of near-field overpressure is mainly studied. Finally

a supersonic aircraft aerodynamic configuration with parallel shock design characteristics is selected. On the basis of this aerodynamic configuration

combined with AMDEsign

a flow field sonic boom coupled with optimization design software

under the condition of specified sonic boom signal with low perceived level noise

the large-scale design variable numerical optimization of the supersonic aerodynamic configuration is realized through the efficient reverse design of far-field sonic boom signal

and the perceived noise level is greatly reduced. The optimized configuration shows multiple weak waves. The effectiveness of design techniques has been verified. The research work can provide a positive reference value for the researchers who are engaged in the low sonic boom aerodynamic configuration design

and provide technical support for the future research and development of supersonic civil aircraft.

关键词

Keywords

references

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