摘要
基于测量基线柱坐标推导了深空航天器赤经、赤纬的信息阵和协方差矩阵,定量计算了干涉延迟测量精度、航天器赤纬及基线几何构型对月球航天器赤经赤纬测量精度的数值关系。根据计算结果,分析了三种因素对确定航天器角误差的影响。提出了基线组合赤经、赤纬精度因子的概念,重点分析了基线几何构型对确定航天器角位置的影响。在航天器视向距离无误差的条件下,推导了航天器三维定位误差与测角误差的协方差矩阵,定量计算了不同干涉延迟精度下月球航天器的三维定位误差。计算及分析结果对于我国未来月球及深空任务的测控分析支持具有重要参考价值。
The information array and covariance matrix for right ascension and declination of lunar and deep space spacecraft are derived based on the cylindrical coordinates of mearsuring baselines.The numerical relations between the precision of right ascension and declination and the precision of interferometric delay,the geometrical configuration of the baselines,as well as the angular position of the spacecraft are calculated.The influence of the three factors on the angular precision is analyzed.The influence of the geometrical configuration of the baselines on the angular precision is discussed in detail based on the concept of the dilution of precision(DOP).The three dimension position determination covariance matrix of spacecraft based on the angular errors is derived,and the position errors of lunar spacecraft are calculated for different precision of interferometric delay.
出处
《飞行器测控学报》
2010年第2期85-90,共6页
Journal of Spacecraft TT&C Technology
关键词
甚长基线干涉
测角精度
跟踪
VLBI
Angular Determination Accuracy
Tracking
