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

作　　者：刘刚[1] 黄江涛[1] 周铸[1] 陈作斌[1] 高正红[2] 钟世东[1] 肖涵山[1] LIU Gang;HUANG Jiangtao;ZHOU Zhu;CHEN Zuobin;GAO Zhenghong;ZHONG Shidong;XIAO Hanshan(China Aerodynamics Research and Development Center,Mianyang 621000,China;School of Astronautics,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[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

出　　处：《空气动力学学报》2020年第5期858-865,I0001,共9页Acta Aerodynamica Sinica

基　　金：基础与前沿技术基金重点项目(PJD20190095);装备预先研究项目(41406030301)。

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。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 nearfield 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：声爆预测 流场/声爆耦合伴随 反设计 等效面积分布 气动布局 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]