Authors: Congshan Qu, Hualong Xu, Ying Tan
Addresses: Xi'an Research Institute of Hi-tech, Hongqing Town, Xi'an, 710025, China. ' Xi'an Research Institute of Hi-tech, Hongqing Town, Xi'an, 710025, China. ' Xi'an Research Institute of Hi-tech, Hongqing Town, Xi'an, 710025, China
Abstract: Strapdown inertial navigation system (SINS) integrated with celestial navigation system (CNS) yields reliable mission capability and enhanced navigation accuracy for spacecrafts. A novel innovation-based adaptive estimation unscented Kalman filter (UKF) to solve the degradation performance caused by CNS unstable measurement disturbances in the SINS and CNS hybrid system is presented in this paper. The proposed adaptive unscented Kalman filter (AUKF) is based on the maximum likelihood criterion for the proper computation of the filter innovation covariance and hence of the filter gains. After having deduced the proposed AUKF algorithm theoretically in detail, the approach is tested in the SINS/CNS integrated navigation system. Numerical simulation results show that the adaptive unscented Kalman filter outperforms the extended Kalman filtering (EKF) and conventional UKF with higher accuracy and robustness. It is demonstrated that this proposed approach is a valid solution to the unknown changing measurement noise in the non-linear filter.
Keywords: adaptive filtering; nonlinear filtering; unscented Kalman filters; integrated navigation; SINS/CNS integration; strapdown inertial navigation systems; celestial navigation systems; reliability; mission capability; navigation accuracy; spacecraft navigation; space missions.
International Journal of Computer Applications in Technology, 2011 Vol.41 No.1/2, pp.109 - 116
Available online: 01 Sep 2011 *Full-text access for editors Access for subscribers Purchase this article Comment on this article