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Error modeling of bias-type parameters for TOPEX orbit determination.

机译:用于TOPEX轨道确定的偏置类型参数的误差建模。

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摘要

The TOPEX mission has a requirement for a radial orbit accuracy of 13 cm over a 10-day period. To achieve this level of accuracy, accurate dynamic and measurement models are required. A large portion of the orbit error is derived from the uncertainty in the apriori values of the constant model parameters, most notably the geopotential coefficients. In this study, the major sources of model error affecting the orbit accuracy of TOPEX are identified. This includes the use of the full calibrated covariance matrix of the nominal geopotential model.;The results of the parameter identification study are used to design an optimal filter for orbit determination. The primary source of orbit error for TOPEX is identified as the geopotential model error followed by error in the solar radiation pressure coefficient. The optimal filter that is derived in terms of the accuracy of the filter estimates is one that includes the initial conditions of the orbit, single arc parameters for the coefficient of drag and the reflectivity coefficient of solar radiation pressure and multiple-arc parameters for the density correction model.;The accuracy of orbit determination for TOPEX is limited by the geopotential model error which is characterized by the calibrated geopotential covariance matrix. Since the geopotential plays a dominant role in determining the radial orbit accuracy of TOPEX, the methods by which the geopotential covariance matrices are calibrated are reviewed in this study. The conventional methods calibrate the covariance matrix with respect to surface gravity and satellite altimeter data.;A new method is proposed that would adjust the formal covariance matrix generated by a gravity model solution for systematic and random errors that affect the orbit accuracy. Expressions for the consider adjusted covariance matrix are derived for both, the classical least squares and the square-root D-U-Z formulations. The method is applied to generate a consider adjusted covariance matrix of the PGTF2 geopotential model for the TOPEX mission.
机译:TOPEX任务要求在10天内的径向轨道精度为13厘米。为了达到这种精确度,需要精确的动态和测量模型。轨道误差的很大一部分来自恒定模型参数的先验值的不确定性,最显着的是地势系数。在这项研究中,确定了影响TOPEX轨道精度的模型误差的主要来源。其中包括使用标称地势模型的完整校准协方差矩阵。参数识别研究的结果用于设计用于确定轨道的最佳滤波器。 TOPEX轨道误差的主要来源被确定为地势模型误差,其后是太阳辐射压力系数误差。根据滤波器估计的精度得出的最佳滤波器包括轨道的初始条件,阻力系数的单弧参数和太阳辐射压力的反射系数以及密度的多弧参数。 TOPEX的轨道确定精度受到地势模型误差的限制,该误差由校准的地势协方差矩阵表征。由于地势在确定TOPEX的径向轨道精度中起着主导作用,因此本文对校准地势协方差矩阵的方法进行了综述。常规方法针对地面重力和卫星高度计数据校准协方差矩阵。提出了一种新方法,该方法将针对影响轨道精度的系统性和随机误差调整重力模型解决方案生成的形式协方差矩阵。对于经典最小二乘和平方根D-U-Z公式,都得出了考虑调整后的协方差矩阵的表达式。该方法适用于为TOPEX任务生成PGTF2势能模型的经考虑调整的协方差矩阵。

著录项

  • 作者

    Rajasenan, C.;

  • 作者单位

    The University of Texas at Austin.;

  • 授予单位 The University of Texas at Austin.;
  • 学科 Engineering Aerospace.;Geodesy.
  • 学位 Ph.D.
  • 年度 1989
  • 页码 241 p.
  • 总页数 241
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

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