利用恒星与地磁场确定卫星自主轨道

徐国栋; 李鹏飞; 董立珉; 侯天蕊

doi:10.3788/OPE.20142205.1280

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利用恒星与地磁场确定卫星自主轨道

微纳技术与精密机械 | 更新时间：2020-08-13

- 利用恒星与地磁场确定卫星自主轨道
- Determination of satallite autonomous orbit based on star light and geomagnetic field
- 光学精密工程 2014年22卷第5期页码：1280-1288
- 作者机构：
  
  哈尔滨工业大学卫星技术研究所,黑龙江哈尔滨,150001
- 作者简介：
- 基金信息：
  
  国家863高技术研究发展计划资助项目（No.2008AA8051602）()
- DOI：10.3788/OPE.20142205.1280
  中图分类号： V241.6;V448.22
- 收稿日期：2013-12-05，
  
  修回日期：2014-01-25，
  
  纸质出版日期：2014-05-25
- 稿件说明：
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徐国栋, 李鹏飞, 董立珉等. 利用恒星与地磁场确定卫星自主轨道[J]. 光学精密工程, 2014,22(5): 1280-1288

XU Guo-dong, LI Peng-fei, DONG Li-min etc. Determination of satallite autonomous orbit based on star light and geomagnetic field[J]. Editorial Office of Optics and Precision Engineering, 2014,22(5): 1280-1288
徐国栋, 李鹏飞, 董立珉等. 利用恒星与地磁场确定卫星自主轨道[J]. 光学精密工程, 2014,22(5): 1280-1288 DOI： 10.3788/OPE.20142205.1280.

XU Guo-dong, LI Peng-fei, DONG Li-min etc. Determination of satallite autonomous orbit based on star light and geomagnetic field[J]. Editorial Office of Optics and Precision Engineering, 2014,22(5): 1280-1288 DOI： 10.3788/OPE.20142205.1280.

摘要

提出一种适用于低轨道卫星的自主导航方法。与以往采用星光角距作为观测量的方法不同，该方法利用卫星平台中常见的星敏感器和地磁敏感器确定卫星实时轨道参数；通过对星敏感器的观测数据进行适当转换，将卫星位置单位矢量观测方程转换为线性化方程；对地磁场强度与轨道高度的关系进行拟合，利用磁强计观测数据求取地心距；采用拉格朗日差值算法确定卫星初轨，为滤波器提供初值。由于二体轨道动力学模型的一阶线性化近似引入的系统模型误差影响了滤波器性能，而一阶导数函数值的线性组合可替代高阶导数的函数值，并降低计算量，所以本文在扩展KALMAN滤波器的设计过程中，对状态方程进行了高阶线性化处理，从而提高了滤波器状态方程的离散化精度。最后，用仿真实验验证了这种低轨卫星轨道确定方法的有效性与实用性。

Abstract

An autonomous navigation method suitable for low orbit satellites is proposed. Different from traditional method that takes a start light angle as the observed variable

the method determines the real time orbital parameters by a start sensor and a geomagnetism sensor

and converses the unit vector observation equation of satellite position into linear equations by converting the observation data from the start sensor appropriately. With fitting the relationship of magnetic field strength and orbit height

it obtains the geocentric distance by using a magnetometer. Moreover

it determines the satellite initial orbit by Lagrange difference algorithm to provide initial value for the filter. As the performance of the filter is effected by the system model error caused from the first-order linear approximation of two body dynamic orbit model

and the high order derivative function values can be replaced by a linear combination of one order derivative function values

this paper processes the state equation by a higher order linearity in design of the KALMAN filter to reduce the calculation. By proposed method

the discretized accuracy of state equation for the filter is improved greatly. Finally

a simulation experiment is performed

which verifies that the method is effective and feasible.

关键词

Keywords

references

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