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基于蒙特卡罗方法和区域分解法,建立低地球轨道空间环境航天器表面原子氧通量密度和积分通量的数学模型。模型考虑了航天器表面几何构型、原子氧数密度和分析热运动、地球自转对航天器速度的影响以及轨道运行参数。通量密度分布的求解是通过其微分方程的对于独立变量分子运动速度和与表面速度矢量合成的积分得到,积分通量是通过沿轨道时间积分来实现。与此同时,得到了沿入射攻角变化原子氧分布的最大值和最小值。计算结果表明:通量分布伴随入射攻角增大而急剧下降,在迎风面达到最大值,背风面最小值。入射攻角是影响分布计算结果的重要因素。计算误差与NASA-LDEF飞行试验实验结果吻合较好。
Based on the Monte Carlo method and the regional decomposition method, a mathematical model of atomic oxygen flux density and integral flux on the surface of spacecraft in low Earth orbit space environment is established. The model takes into account the geometry of the spacecraft surface, the density of atomic oxygen and the analysis of thermal motion, the influence of the Earth's rotation on the spacecraft's speed, and orbital parameters. The solution of the flux density distribution is obtained by integrating the velocity of the molecular motion of the independent variable with the surface velocity vector in its differential equation, and the integral flux is obtained by integrating along the track time. At the same time, the maximum and minimum values of atomic oxygen distribution along the incident angle of attack were obtained. The calculation results show that the flux distribution decreases sharply with the incident angle of incidence increasing, reaching the maximum on the windward side and the minimum on the leeward side. The incident angle of attack is an important factor affecting the distribution calculation results. The calculation error is in good agreement with the NASA-LDEF flight test results.