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Multisensor fusion for an experimental airship based on strong tracking filter

Multisensor fusion for an experimental airship based on strong tracking filter
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摘要 To improve the independent ability of attitude determination and positioning for an unmanned experimental airship platform, a micro inertial measurement system (MIMS) is expected to integrate with the existing system, which incorporates a digital magnetic compass and a differential pseudorange GPS receiver. The navigation error of the low-precision MIMS will be calibrated using nondrift DGPS receiver and magnetic compass. This paper proposes an adaptive strong tracking filter to perform multisensor fusion to assure state-error estimation of convergence under some uncertain conditions. These uncertainties include model simplification, unknown microsensor stochastic characteristics, a large-scale initial filtering parameter variation, and state sudden change. Monte Carlo simulations demonstrate the filter has strong robustness to all the uncertainties mentioned above. By this filtering approach, the navigation errors of MIMS are limited to a certain range. Accordingly, the whole integrated measurement system will respond to dynamics, and its automotive navigation ability is also enhanced. To improve the independent ability of attitude determination and positioning for an unmanned experimental airship platform, a micro inertial measurement system (MIMS) is expected to integrate with the existing system, which incorporates a digital magnetic compass and a differential pseudorange GPS receiver. The navigation error of the low-precision MIMS will be calibrated using nondrift DGPS receiver and magnetic compass. This paper proposes an adaptive strong tracking filter to perform multisensor fusion to assure state-error estimation of convergence under some uncertain conditions. These uncertainties include model simplification, unknown microsensor stochastic characteristics, a large-scale initial filtering parameter variation, and state sudden change. Monte Carlo simulations demonstrate the filter has strong robustness to all the uncertainties mentioned above. By this filtering approach, the navigation errors of MIMS are limited to a certain range. Accordingly, the whole integrated measurement system will respond to dynamics, and its automotive navigation ability is also enhanced.
出处 《Journal of Systems Engineering and Electronics》 SCIE EI CSCD 2005年第2期363-368,共6页 系统工程与电子技术(英文版)
基金 ThisprojectwassupportedbyShanghaiJiaotongUniversity"985"foundation(415011102).
关键词 micro interial measurement system GPS magnetic compass STF extended Kalman filter. micro interial measurement system, GPS, magnetic compass, STF, extended Kalman filter.
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  • 1冯绍军.低成本IMU/GPS组合导航系统研究[M].南京:南京航空航天大学,1999,1..
  • 2段志勇.GPS航姿系统及多天线GPS/惯性组合导航技术研究[M].南京:南京航空航天大学,2000..

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