| 地空导弹厚壁气动加热温度计算 |
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| 引用本文： | 张成红,张成光.地空导弹厚壁气动加热温度计算[J].沈阳航空工业学院学报,2010,27(1):14-17. |
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| 作者姓名： | 张成红 张成光 |
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| 作者单位： | 1. 中国航天○六一基地江南航天机电设计研究所,贵州,贵阳,550009
2. 河南工业职业技术学院,河南,南阳,473009 |
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| 摘 要： | 导弹在飞行中，弹体周围的气流温度会升高，弹体表面被加热；飞行速度越高，加热越严重。介绍了地空导弹厚壁气动加热的工程计算方法，包括空气绕流参数、热交换系数与弹体头部的表面温度计算公式。
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| 关 键 词： | 厚壁 气动加热 绕流参数 热交换系数 |
Surface heating temperature caculation of landed missile heavy wall aerodynamic |
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| ZHANG Cheng-hong,ZHANG Cheng-guang.Surface heating temperature caculation of landed missile heavy wall aerodynamic[J].Journal of Shenyang Institute of Aeronautical Engineering,2010,27(1):14-17. |
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| Authors: | ZHANG Cheng-hong ZHANG Cheng-guang |
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| Institution: | ZHANG Cheng - hong ZHANG Cheng - guang (1. Institute of Jiangnan Space Mechelectronic Design,061 base of CSST, Guizhou Guiyang 550009 ;2. Institute of Henan Industry Professial Technology , Henan Nanyang 473009) |
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| Abstract: | When the missile flying, stream temperature around the missile will be raised, and the missile will be heated. Higher the missile flying velocity is, more serious the surface heating is. This paper introduce the air surface engineering calculation method of missile aerodynamic heating, including air circumferential flow parameter, themal exchange coefficient and the missile body forehead surface temperature formula. |
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| Keywords: | thick wall aerodynamic heating air circumferential flow parameter： themal exchange coefficient |
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