低地球轨道航天器不同攻角原子氧通量密度计算模型  

Model of Atomic Oxygen Fluence for Different Spacecraft Surface in Low Earth Orbit

作　　者：郑阔海[1] 李中华[1] 王敬宜[1] 赵琳[1] 

机构地区：[1]兰州物理研究所真空低温技术与物理国家级重点实验室,兰州730000

出　　处：《宇航学报》2010年第7期1855-1863,共9页Journal of Astronautics

摘　　要：低地球轨道原子氧与航天器表面材料相互作用,可导致材料因氧化剥蚀而发生性能衰退,是低地球轨道航天器设计者最关心的环境因素。本文扼要地介绍了兰州物理研究所原子氧实验室采用VB语言编制的"航天器原子氧通量密度计算模型",该模型以地球大气模式为核心,采用麦克斯韦速度分布对航天器不同攻角遭受到的原子氧进行计算,计算过程中考虑了大气风的影响。模型还可跟踪卫星在轨运行,对不同表面遭受的原子氧通量进行实时计算。计算结果与NASA的原子氧计算模型FluxAV相接近,可为卫星设计者在材料选择时提供数据参考。Atomic oxygen is the most important environmental element spacecraft designer cared in LEO which can oxidize materials by impaction. This paper presents the atomic oxygen calculation model briefly developed by the Lab. of atomic oxygen effects protection,Lanzhou Institute of Physics with VB program. The model uses atmosphere model as its calculation core,and can calculate atomic oxygen fluence/flux of different surface with Maxwell velocity distribution,and the influence of the atmosphere wind is also involved. The model can also give the real-time atomic oxygen fluence/flux of different surface by tracing satellite orbiting. The deviation of the results from the similar model,FluxAV of NASA,is negligible,so it can be used as a reference for spacecraft designer.

关 键 词：LEO 原子氧 计算模型 大气模型 LDEF FluxAV 

分 类 号：V520.1[航空宇航科学与技术—人机与环境工程]