Determination of satallite autonomous orbit based on star light and geomagnetic field

XU Guo-dong; LI Peng-fei; DONG Li-min; HOU Tian-rui

doi:10.3788/OPE.20142205.1280

您当前的位置：

首页 >

文章列表页 >

Determination of satallite autonomous orbit based on star light and geomagnetic field

更新时间：2020-08-13

- Determination of satallite autonomous orbit based on star light and geomagnetic field
- Optics and Precision Engineering Vol. 22, Issue 5, Pages: 1280-1288(2014)
- 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：
- DOI：10.3788/OPE.20142205.1280
  CLC： V241.6;V448.22
- Received：05 December 2013，
  
  Revised：25 January 2014，
  
  Published：25 May 2014
- 稿件说明：
移动端阅览
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

WHITE R L, GUONLEY R B.Satellite Autonomous Navigation with SHAD [M].The Charles Stark Draper Laboratory, 1987.

MERTIKAS S, RIZOS C.On-line detection of abrupt changes in the carrier-Phase measurements of GPS [J].Journal of Geodesy, 1997, 71:469-482.

MONTENBRUCK O, HELLEPUTTE T, REMCO KROES, et al..Reduced-dynamic orbit determination using GPS code and carrier measurements[J].Aerospace Science and Technology, 2005, 9(13):261-271.

李勇, 魏春岭. 卫星自主导航技术发展综述[J]. 航天控制, 2002, 20(2):70-74. LI Y, WEI CH L.Review on the development of autonomous navigation technigues for satellites [J].Aerospace Control, 2002, 20(2):70-74.(in Chinese)

王鹏, 张迎春. 基于星敏感器/红外地平仪的自主导航算法研究[J]. 系统工程与电子技术, 2008, 30(8):1514-1518. WANG P, ZHANG Y CH.Research on autonomous ravigation algorithm based on star sensor and infrared horizon sensor [J].Systems Engineering and Electronic, 2008, 30(8):1514-1518.(in Chinese)

WIEGAND M.Autonomous satellite navigation via kalman filtering of magnetometer data[J].Acta Astronautica, 1996, 38(4):395-403.

SUNEEL I S.The Use of Variable Celestial X-RAY Sources For Spacecraft Navigation.Maryland:Department of Aerospace Engineering University of Maryland, 2005:180-185.

马剑波, 徐劲, 曹志斌. 一种利用星敏感器的卫星自主定轨方法[J]. 中国科学G辑, 2005, 35(2):213-224. MA J B, XU J, CAO ZH B.Use of a star sensor based autonomous orbit determination of satellites[J].Science in china ser.G Physics, Mechanics & Astronomy, 2005, 35(2):213-224.(in Chinese)

MICHAEL A, JOSEPH B.Optical navigation system.AIAA Guidance Navigation and Control Conference.Orgon:American Institute of Aeronautics and Astronautics Press, 2010:3462-3484.

宁晓琳, 王华龙. 一种星光折射卫星自主导航系统方案设计[J]. 宇航学报, 2012, 33(11):1601-1611. NING X L, WANG L H.A scheme design of satellite autonomous navigation system based on stellar refraction[J].Journal of Astronautics, 2012, 33(11):1601-1611.(in Chinese)

SHORSHI G, BAT-ITZHACK Y.Satellite autonomous navigation based on magnetic field measurements [J].Joumal of Guidance, Control and Dynamics, 1995, 18(4):843-850.

DEUTSCHMANN J K.Evaluation of attitude and orbit estimation using actual earth magnetic field data [J].Journal of Guidance, Control and Dynamics, 2001, 24(3):616-623.

孙俊, 张世杰, 李葆华. 利用地球紫外和恒星可见光的卫星自主导航[J]. 光学精密工程, 2013, 21(5):1192-1198. SUN J, ZHANG SH J, LI B H.Autonomous navigation based on star light and ultraviolet earth sensors [J].Opt.Precision Eng., 2013, 21(5):1192-1198.(in Chinese)

CARLOS ROITHMAYR.Contributions of spherical hamonics magnetic and gravitational fields.USA:NASA, 1996:EG2-96-02.

钟兴, 贾继强, 金光, 等. 机载导航白天星敏感器的探测性能及总体设计[J]. 光学精密工程, 2011, 19(12):2900-2906. ZHONG X, JIA J Q, JIN G, et al..Detecting performance and overall design of airborne daylight star sensor for navigation [J].Opt.Precision Eng., 2011, 19(12):2900-2906.(in Chinese)

SIMON J, JEFFREY UHLMANN.A new method for the Nonlinear Transformation of means and covariances in filters and estimators[J].IEEE Transactions on Automatic Control, 2000, 45(3):479-480.

张池平.计算方法 [M].北京:科学出版社, 2006:94-99. ZHANG CH P.Calculation Method[M].Beijing:Science Press, 2006:94-99.

Views

464

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Kalman filter based output feedback predictive control for piezoelectric ceramic actuators

Calibration and correction of geometric errors in laser tracker

Model establishment and error correction of FMCW lidar

Multi-machine cooperative passive localization based on MEMS/GNSS

A fast and robust method for detecting elliptical character of cooperative targets in industrial complex background

Related Author

YU Shuyou

TAN Li

LI Jianpu

FENG Yangyang

LIU Dongmei

LIN Baojun

SUN Shaoyu

WANG Shan

Related Institution

College of Electronic and Information Engineering， Changchun University

Key Laboratory of Industrial Internet of Things and Networked Control， Ministry of Education， Chongqing University of Posts and Telecommunications

Department of Control Science and Engineering， Jilin University

University of Chinese Academy of Sciences

Institute of Microelectronics of the Chinese Academy of Sciences

AI问答

Address：No.3888 Dong Nanhu Road, Changchun, Jilin, China Postal code：130033
Tel：0431-86176855 Email：gxjmgc@ciomp.ac.cn
Technical support is provided by Beijing Founder electronics co., LTD 吉ICP备11002662号-17 京公网安备11010802024621
It is recommended to read the content of this site in Chrome&IE9+. Please switch to extreme mode in browser 360.
Cookies We use cookies to help provide and enhance our service and tailor content. By continuing, you agree to the use of cookies.

⁰