Efficient satellite orbit modelling using pseudo-stochastic parameters
Efficient satellite orbit modelling using pseudo-stochastic parameters
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DOI：
10.1007/s00190-006-0072-6
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发表时间：
2006-10-01
影响因子：
4.4
通讯作者：
Mervart, L.
中科院分区：
文献类型：
--
作者：
Beutler, G.;Jaeggi, A.;Mervart, L.
如果作用在人造地球卫星上的力场不能先验地以足够的精度表示其观测结果的精度水平，则可以在定轨过程中引入所谓的伪随机参数，例如在用户自定义的时间点上的瞬时速度变化，或在用户自定义的相邻时间子区间上的分段恒定加速度，或在相邻时间子区间上的分段线性和连续加速度。基于标准最小二乘的与这些参数化相关的过程已经建立得很好，但如果伪随机参数的数量变得很大，它们就会变得低效（缓慢）。提出了两种求解伪随机参数下轨道确定问题的有效方法。所得结果与传统最小二乘算法的结果一致。第一种高效算法还提供了完整的方差-协方差矩阵；第二种更有效的算法，只是其中的一部分。
If the force field acting on an artificial Earth satellite is not known a priori with sufficient accuracy to represent its observations on their accuracy level, one may introduce so-called pseudo-stochastic parameters into an orbit determination process, e.g. instantaneous velocity changes at user-defined epochs or piecewise constant accelerations in user-defined adjacent time subintervals or piecewise linear and continuous accelerations in adjacent time subintervals. The procedures, based on standard least-squares, associated with such parameterizations are well established, but they become inefficient (slow) if the number of pseudo-stochastic parameters becomes large. We develop two efficient methods to solve the orbit determination problem in the presence of pseudo-stochastic parameters. The results of the methods are identical to those obtained with conventional least-squares algorithms. The first efficient algorithm also provides the full variance-covariance matrix; the second, even more efficient algorithm, only parts of it.