大气阻力摄动计算方法及误差分析  

CALCULATION METHODS FOR ATMOSPHERIC DRAG PERTURBATION AND ERROR ANALYSIS

作　　者：刘亚英[1] 戎鹏志[1] 

机构地区：[1]中国科学院紫金山天文台,上海卫星工程研究所

出　　处：《中国空间科学技术》1996年第2期7-13,共7页Chinese Space Science and Technology

摘　　要：探索了大气阻力摄动精密计算方法，以提高卫星空间位置的预报精度。根据大气阻力摄动的基本原理，给出两种摄动计算方法，即半分析半数伍方法和数值积分方法。选用Ｍ种高层大气模型：ＣＩＲＡ－１９８６、ＣＩＲＡ－１９７２和ＤＴＭ模型，分析比较了太阳活动中高年水平（Ｆ１０．７取为１５０，２００，２５０）和１０％～２０％的模型误差引起卫星空间位置的误差δｐ。结果显示：①太阳活动Ｆ１０．７的大小对δｐ的影响明显，在同样模型误差情况下，δＰ随Ｆ１０．７的增大而成倍地增大；②大气模型与实际之差引起的空间位置误差δｐ随模型误差增大而线性地增大；③不同大气模型引起的卫星空间位置误差δｐ一般不大，但在Ｆ１０．７≥２００时，ＤＴＭ模型与ＣＩＲＡ模型差异较大。n order to improve the accuracy of the prediction of satellite's orbit, the calculation methods of atmospheric drag perturbation are studied. On the basis of the principle of atmospheric drag perturbation this paper describes two methods: numerical method and combining both of analytical and numerical method. The error δp of the satellite's position in orbit due to various level (F10.7 of 150, 200 and 250) of solar activity and the model's error of 10%- 20% are analyzed for three kinds of upper atmosphere models: CIRA-1986, CIRA-1972 and DTM. The results show that: ① The effect of the solar activity level on the error δp is obvious. The error δp increases fast with F10.7 in case of given atmosephere model error. ② The error δp increases proportionally as the difference between the model and the reality increases. ③ The error a, due to the variety of atmosphere model is not noticeable in general, but when F10.7 is greater than 200 the difference between DTM model and CIRA model is very noticeable.

关 键 词：阻力 摄动 大气模式 误差分析 人造卫星 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]