In order to overcome the deficiencies of current navigation technologies of cruise missile, a navigation method using geomagnetic field information was presented. A navigation filter based on the unscented Kalman I liter algorithm was designed by taking the international geomagnetic reference field as the geomagnetic field model, the geomagnetic field vectors and the flight height as observed vari?ables, and combining the missile motion model with the geomagnetic field model. The observability and observable degree of the navigation system were analyzed in detail by the observability matrix and the singular value decomposition method. The location and speed of cruise missile were simulated by the navigation filter. The simulated results show that the navigation precision with high order geo?magnetic field model is better than that with low order geomagnetic field model; the smaller the ob?served noise intensity is, the higher the navigation precision is. The method provides better filter con?vergence, stability and moderate navigation precision for autonomous navigation in the initial and mid?course phase guidances of cruise missile.
Key words
control and navigation technology of aerocraft /
geomagnetic navigation /
unscented Kalman niter /
cruise missile /
international geomagnetic reference field /
observability
{{custom_keyword}} /
{{custom_sec.title}}
{{custom_sec.title}}
{{custom_sec.content}}
References
[I] Thienel J K, Harman R R. Results of the magnetometer naviga?tion (MAGNAV) in flight experiment[ Q]// AIAA/AAS Astrody- namics Specialist Conference and Exhibit, Providence : Rhode Is?land, 2004: 1-18.
[2] Julier S J, Unlmann J K. A new extension of the Kalman filter to nonlinear systems[C]. The Proceedings of Aerosense: The Ilth Int Symp on Aerospace/Defense Sensing, Simulation and con?trols, Orlando : Florida, 1997 : 54 — 65.
[3] Julier S J, Uhlmann J K, Durrant-Whyte H F. A new method of the nonlinear transformation of means and covariances in filters and estimators[ J ]. IEEt iTrans on Automatic Control,2000, 45(3) : 477-482.
[4] Julier S J, Uhimann J K. Unscented filtering and nonlinear esti- mation[j]. Proceedings of the IEEE, 2004,92(3) :401 — 421.
[5] Julier SJ. The scaled unscented transformation [C]//Proc of American Control Conf Jefferson City,US: Achorage, 2002, 6: 4555-4559.
[6] 王亶文.国际地磁参考场在中国大陆地区的误差分析[J].地 球物理学报,2003,46(2) : 171 - 174.
WANG Dan-wen. Analysis of the international geomagnetic reier- ence xield error in the しhina continent [ J]? Chinese Journal of Geophysics, 2003,46(2) : 171 - 174. (in Chinese)
[7] 高德章.国际地磁参考场及其计算[J].海洋石油,1999,3:34 -42.
GAO De-zhang ? international geomagnetic reierence fieia & com?putation [ J ]? Marine Petroleum, 1999, 3: 34 — 42. (in Chinese)
[8] Goshen-Msekin D, Bar-Itzhack I Y. Observability analysis of piece-wise constant systems-part I : theory [ J ]. IEEE Trans on Aerospace and Electronics Systems, 1992,28(4) : 1056 - 1067.
[9] Reif K, Gunther S. Stochastic stability of the discrete-time ex?tended Kalman filter [ J ] . IEEE Trans on Automatic Control, 1999, 44(4):714-728.
[10] Chen Zhe. Local observability and its application to multiple measurement estimation [ J ]. Industrial Electronics, IEEE Trans, 1991,38(6) :491 - 496.
[11] Goshen-Msekin D,Bar-Itzhack I Y. Observability analysis of piece-wise constant systems-part II : application to inertial navi?gation in-flight alignment [ J ]. IEEE Trans on Aerospace and Electronics Systems, 1992,28(4) : 1068 — 1075.
[12] 吴海仙,俞文伯,房建成.高空长航时无人机SINS/CNS组合 导航系统仿真研究[J].航空学报,2006,27(2) :299 - 304. WU Hai-xian, YU Wen-bo, FANG Jian-cheng. Simulation of SINS/ CNS integrated navigation system used on high altitude and. long-flight-time unpiloted, aircraft [J ] ? Acta Aeronautica EtAstronautica Sinica, 2006,27(2) :299 - 304. (in Chinese)
[13] Goidenberg F. Geomagnetic navigation beyond magnetic compass [C]. IEEE PLANS 2006, San Diego, California, 2006 : 684 - 694.
{{custom_fnGroup.title_en}}
Footnotes
{{custom_fn.content}}