摘要
本文对人造卫星测角观测资料的拉普拉斯初轨计算方法进行了两点重要改进: (1) 将条件方程的形式进行了变换,使条件方程受方位角误差的影响很小,从而提高初轨测定精度,并改善整个计算过程的收敛性; (2) 对初值选择方式进行了改进,使其适用于任意轨道偏心率,可以显著地改善迭代收敛过程. 实际计算表明,只要具有适当精度的观测弧段和数据采集密度,这种改进型的拉普拉斯方法是可靠、有效的.
This paper presents two main improved points of the Laplacian method for computing preliminary orbits, in which the directional observing data are used. (1) The form of the condition equations is changed,, and it makes the condition equations affected little by the azimuthal errors, thereby the accuracy of the preliminary orbits determination is improved, and the convergence of the computational process is also improved. (2) The way for selecting initial values is improved, this makes it suit to any orbital eccentricity, and greatly improve the convergence process of iteration. The practical computational results show: so long as we have suitable arc length and sampling density of observational data, this improved Laplacian method is reliable and effective.
出处
《天文学报》
CSCD
北大核心
1991年第1期62-72,共11页
Acta Astronomica Sinica
关键词
人造
地球卫星
轨道
计算
Artificial Satellite—Initial orbit determination
