一种有效提高超大偏心率轨道初轨确定精度的新方法

A New Method for Initial Orbit Determination to Improve Accuracy of Extra-large Eccentricity Orbits

针对某型号航天器的运行轨道偏心率大、轨控结束后可用于初轨确定的测轨数据少的特点，提出了一种能有效提高超大偏心率短弧段初轨确定精度的新方法。该新方法将轨道改进的思想融入初轨计算方法中，使之既适用于各种偏心率轨道的初轨计算，也适用于各种偏心率轨道的长弧段、多圈、多站数据的轨道改进；解决了传统初轨确定方法超大偏心率轨道短弧段初轨确定误差偏大的问题。通过任务实测数据的检验，新方法适用于各种偏心率轨道，并且超大偏心率轨道的初轨确定精度明显优于传统方法。

The problem of very large orbital eccentricity and availability of only a small amount of data for initial orbit determination is encountered in a project. To solve the problem, a new IOD method is presented in this paper to effectively improve IOD accuracy of extra-large eccentricity orbits. The new method introduces the idea of orbit improvement into IOD, and it not only suits IOD with short arc of extra-large eccentricity orbits, but also suits orbit improvement for orbits of any eccentricity with data of long are or multi-arc and multi-station. It also solves the problem that error of traditional IOD method is too large for extra-large eccentricity orbits. Tested with actual mission data, the new method fits well into orbits of any eccentricity, and the IOD accuracy for orbits of extra-large eccentricity is significantly better than traditional IOD methods.