返回式航天器轨道周期变率确定及预报的数值方法  

Numerical Method of Orbital Period Rate Determination and Prediction for Recoverable Spacecraft

作　　者：秋宏兴[1] 王秀红[2] 吴连大[1] 祝开建[2] 

机构地区：[1]中国科学院南京紫金山天文台,南京210008 [2]西安卫星测控中心,西安710043

出　　处：《中国空间科学技术》2007年第3期7-12,共6页Chinese Space Science and Technology

摘　　要：对返回式航天器进行变轨控制计算时要用到平均轨道周期变率,而数值法定轨通常求解的是大气阻力系数,无法直接得到平均轨道周期变率。文章通过建立航天器精密动力学模型、数值积分器、瞬时轨道根数到平均轨道根数的转换算法和平均周期序列多项式拟合算法,提出了一种基于数值法精密轨道确定和预报计算平均轨道周期变率的数值方法。Numerical method of orbit determination usually can not directly obtain mean orbit period rate used to calculate orbit maneuver strategy for recoverable spacecraft, but can solve atmospheric drag coefficient. Through the creation of sophisticated spacecraft dynamics models, numerical integrator, conversion algorithm from osculating elements to mean elements and polynomial fitting algorithm for mean period series, a calculation method of mean orbit period rate was proposed based on numerical method for precision orbit determination and prediction. Applications for the two spaeecrafts have revealed to the validity of the methodology.

关 键 词：周期变率 数值方法 轨道衰减 大气阻力 返回式航天器 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]