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高速导弹光学窗口外存在激波层,为高度不均匀的高温气体介质。其热辐射效应使红外探测设备获得的红外遥感图像存在退化和畸变。通过对分子热运动的计算,分析高温气体分子、原子辐射吸收系数,将流场数据有限元处理,实现灰气体总体模型与逐线计算方法的改进结合;通过对气体介质求解辐射传递方程,基于离散传递法的思想,推衍出激波层的热辐射强度计算模型;结合光线传输模型寻找导引头探测口径内的视线路径,解析大气热辐射机理,发展激波层热辐射数值计算方法,两种定量计算模型互为比较验证。研究得出激波层热辐射噪声与来流参数之间的关系,并给出了经验公式。
There is a shock wave layer outside the high-speed missile optical window, which is a high-temperature gas medium with a high degree of unevenness. Its thermal radiation effects make the infrared remote sensing images obtained by infrared detection equipment degenerate and distorted. By calculating the molecular thermal motion, the absorption coefficient of high temperature gas molecules and atomic radiation is analyzed, and the flow field data are processed by finite element method to realize the improvement of the general gray gas model and the line-by-line calculation method. By solving the radiative transfer equation for the gas medium, Discrete propagation method, deducing the heat radiation intensity calculation model of the shock wave layer; combining the light transmission model to find the line of sight path within the detection aperture of the seeker, analyzing the mechanism of atmospheric heat radiation and developing the numerical calculation method of heat radiation of shock wave layer, The two quantitative calculation models are compared with each other. The relationship between the heat radiation noise of shock wave layer and the parameters of the incoming flow is obtained, and the empirical formula is given.