高超声速飞行器声载荷风洞试验方法  

Study of Acoustic Loading Testing Method in Wind-tunnel for Hypersonic Vehicle

作　　者：赵小见[1] 陈农[1] 

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《战术导弹技术》2014年第3期23-27,33,共6页Tactical Missile Technology

摘　　要：鉴于高超声速飞行器特有的外形布局和飞行状态限制,高超声速飞行器声载荷试验存在模型头部气动加热较强、弹舱内走线空间有限、弹翼声载荷测量难度较大等困境。针对这些难点问题逐一进行了分析研究,并提出相应解决方案,满足了试验的要求。通过风洞脉动压力试验,获得飞行器表面脉动压力系数分布、频谱特性、相干函数等重要衡量非定常载荷特性的参数,为高超声速飞行器结构设计提供数据支持。Due to its special aerodynamic configuration layout and flight states limitation, some obstacles are encountered, including strong aerodynamic heating on the head of model, limit space for data trans- mission lines and difficulty for acoustic loading testing on the wing. The solutions for these problems were proposed one by one which would meet the demand of wind tunnel testing. Through the wind-tunnel tes- ting, the coefficients which are the scales of the unsteady aerodynamic loading were obtained, including fluctuating pressure coefficient, frequency spectrum character, coherence function, and etc, which would provide data support for hypersonic aircraft structure design.

关 键 词：高超声速 声载荷 风洞 空气动力学 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]