The Research On Autonomous Navigation With Multi-source Information Fusion And System Realization Of Aerospace Vehicle

The Aerospace Vehicle(ASV) has the characteristics that its flight mission is special and its flight environment is complex, so a single navigation system cannot independently provide high-precise parameters for the ASV. Consequently, this paper conducted a research on the autonomous navigation with multi-source information fusion and system realization of Aerospace Vehicle. The research aimed to propose appropriate autonomous navigation system with multi-source information fusion and multi-source data fusion algorithm for the ASV, which provided the theoretical basis and technological support for the engineering implementation of the ASV’s integrated navigation system.To make sure that the ASV can complete the flight mission accurately in the complex environment, the strapdown calculating model in the launch inertial coordinate system was established and the strapdown inertial navigation algorithm was researched aimed at the demand of the high-precision navigation in the launch active period. At the same time, according to the analysis of the demand for the navigation system in different flight periods of the ASV, the overall scheme of the autonomous navigation with multi-source information fusion was designed based on strapdown inertial navigation system in the launch inertial coordinate system, providing the basic gist for the realization of the autonomous navigation system with multi-source information fusion of the ASV.To accomplish multi-source navigation information fusion effectively, aimed at the nonlinear state model of the ASV’s navigation system in the launch inertial coordinate system, the ASV’s integrated navigation system error state equations in the launch inertial coordinate system were established based on the analysis of EKF, and the SINS/GNSS/Star-sensor/Uv-sensor integrated navigation system’s measurement model was established, to evaluate the navigation system error parameters in the launch inertial coordinate system. The simulation results show that the EKF algorithm can supply precise integrated navigation parameters, offering research basis to improve the performance of integrated navigation multi-source information fusion algorithm of the ASV.In order to improve the accuracy of filtering algorithm further in aerospace flight conditions, this paper researched the integrated navigation nonlinear filtering methods. The effect of the integrated navigation system filtering equation’s linearization was analyzed. The UKF and PF based on particles sampling were researched. The ASV’s integrated navigation nonlinear filtering methods based on UKF and PF in the launch inertial coordinate system were designed. The integrated navigation system state parameters were evaluated by UKF and PF. The simulation results show that, compared with EKF, the UKF and PF can improve integrated navigation precision more markedly. It provides theoretical support for the realization of the integrated navigation nonlinear filtering algorithm of the ASV.To verify the overall performance of the ASV’s integrated navigation scheme and the filtering algorithms researched in this paper effectively, the ASV’s integrated navigation system semi-physical simulation verification environment was designed and realized. The algorithm verification software and hardware platform based on PC104 embedded computer were established. It can provide a useful reference for the engineering application of the integrated navigation filtering algorithms researched in this paper.