IMECH-IR  > 高温气体动力学国家重点实验室
高超声速脉冲风洞模型自由飞试验技术
苑朝凯; 孙英英; 姜宗林
Source Publication气体物理
2016-03-15
Volume1Issue:02Pages:55-63
ISSN2096-1642
Abstract风洞模型自由飞试验利用高速相机记录自由飞行模型的运动历程,再根据模型运动特征参数反演模型的气动特性.由于没有支撑系统的干扰,该试验能够较真实地模拟飞行状态,在飞行器静/动稳定特性研究中具有独特的优势.文章在JF-8A高超声速脉冲风洞中开展了10°尖锥模型自由飞试验,并以圆球模型的自由飞运动测量风洞动压,对模型运动特征参数的数字图像提取技术及气动参数的辨识方法等关键技术进行了研究.
Keyword高超声速 脉冲风洞 自由飞试验 动稳定性 尖锥
Language中文
Document Type期刊论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/72094
Collection高温气体动力学国家重点实验室
Recommended Citation
GB/T 7714
苑朝凯,孙英英,姜宗林. 高超声速脉冲风洞模型自由飞试验技术[J]. 气体物理,2016,1(02):55-63.
APA 苑朝凯,孙英英,&姜宗林.(2016).高超声速脉冲风洞模型自由飞试验技术.气体物理,1(02),55-63.
MLA 苑朝凯,et al."高超声速脉冲风洞模型自由飞试验技术".气体物理 1.02(2016):55-63.
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