A new SINS/GPS sensor fusion scheme for UAV localization problem using nonlinear SVSF with covariance derivation and an adaptive boundary layer

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• 作者：Fariz Outamazirt^a ; ^{outamazirt.fariz@yahoo.fr" class="auth_mail" title="E-mail the corresponding author}Author Vitae ; Li Fu^aAuthor Vitae ; Yan Lin^a ; Nemra Abdelkrim^bAuthor Vitae
• 关键词：Adaptive smoothing boundary layer ; Autonomous airborne navigation ; GPS ; Smooth variable structure filter (SVSF) ; Strapdown inertial navigation system (SINS)
• 刊名：Chinese Journal of Aeronautics
• 出版年：2016
• 出版时间：April 2016
• 年：2016
• 卷：29
• 期：2
• 页码：424-440
• 全文大小：4907 K

文摘

The state estimation strategy using the smooth variable structure filter (SVSF) is based on the variable structure and sliding mode concepts. As presented in its standard form with a fixed boundary layer limit, the value of the boundary layer width is not precisely known at each step and may be selected based on a priori knowledge. The boundary layer width reflects the level of uncertainty in the model parameters and disturbance characteristics, where large values of the boundary layer width lead to robustness without optimality and small values of the boundary layer width provide optimality with poor robustness. As a solution and to overcome these limitations, an adaptive smoothing boundary layer is required to achieve greater robustness and suitable accuracy. This adapted value of the boundary layer width is obtained by minimizing the trace of the a posteriori covariance matrix. In this paper, the proposed new approach will be considered as another alternative to the extended Kalman filters (EKF), nonlinear H_∞ and standard SVSF-based data fusion techniques for the autonomous airborne navigation and self-localization problem. This alternative is based on strapdown inertial navigation system (SINS) and GPS data using the nonlinear SVSF with a covariance derivation and adaptive boundary layer width. Furthermore, the full mathematical model of the SINS/GPS navigation system considering the unmanned aerial vehicle (UAV) position, velocity and Euler angle as well as gyro and accelerometer biases will be used in this paper to estimate the airborne position and velocity with better accuracy.