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本文以漫反射理论模型和修正牛顿理论为基础,提出一套计算近地卫星气动力的工程近似方法,推荐二种通用气动函数表。根据本文所介绍的计算公式和函数表格,经过简单算术运算,即可求出各种理论外形(轴对称组合几何体)在轨道运行段和再入大气层过程中气动力系数。大量计算表明:飞行高度在135公里以上时完全可按自由分子流理论计算,飞行高度在80公里以下时完全可按连续流理论计算,中间过渡区可利用自由分子流和连续流的计算值进行半经验修正。
Based on the theory of diffuse reflection and the modified Newton’s theory, this paper presents a set of engineering approximate methods for calculating the aerodynamic force of near-space satellites. Two kinds of general aerodynamic function tables are recommended. According to the calculation formulas and function tables introduced in this paper, the aerodynamic coefficients of various theoretical shapes (combination of axisymmetric geometry) in orbit and reentry atmosphere can be obtained through simple arithmetic operation. A large number of calculations show that when the flight altitude is above 135 km, it can be completely calculated according to the theory of free molecular flow. When the flight altitude is below 80 km, the continuous flow theory can be used. The intermediate transition zone can be calculated by using the free molecular flow and the continuous flow Semi-empirical correction.