| 高超声速飞行器大气数据传感系统关键技术初步分析 |
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| 引用本文： | 杨志红,沈作军.高超声速飞行器大气数据传感系统关键技术初步分析[J].战术导弹控制技术,2009(1). |
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| 作者姓名： | 杨志红 沈作军 |
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| 作者单位： | 北京机电工程研究所,北京100074 |
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| 摘 要： | 高超声速大气数据传感技术的研究和创新已经成为了国外高超声速技术领域的重要研究内容，许多国家在嵌入式大气数据传感系统（flush airdata sensing system，FADS）方面开展了大量的理论和工程试验研究工作。FADS技术通过在机身，通常是头部特定位置布置一组测压孔，实时测量来流压力，与通过CFD计算或风洞试验获得的不同马赫数及角度下的测压点压力分布数学模型进行比较，采用非线性递归算法反推得到攻角、侧滑角度等参数值．
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| 关 键 词： | 大气数据传感系统 高超声速飞行器 数据传感技术 数学模型 |
Primary analysis of key technology on airdata sensing system for hypersonic vehicle |
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| YANG Zhi-hong,SHEN Zuo-jun.Primary analysis of key technology on airdata sensing system for hypersonic vehicle[J].Control Technology of Tactical Missile,2009(1). |
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| Authors: | YANG Zhi-hong SHEN Zuo-jun |
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| Affiliation: | YANG Zhi-hong,SHEN Zuo-jun (Beijing Electromechanical Engineering Research Institute,Beijing 100074,China) |
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| Abstract: | Research and innovation on airdata sensing system (ADSS) for hypersonic vehicle is an important field abroad. Many countries make substantive theoretical and application investigations on flush airdata sensing system (FADS). Laying some orifices on specific nose positions, FADS measures jet pressure, which is compared with distributed mathematical model obtained by CFD or wind tunnel experiment, and angle of attack and angle of sideslip are obtained by nonlinear recursive algorithms. |
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| Keywords: | flush airdata sensing system(FADS) hypersonic vehicle |
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