Optimal Algorithm of Dual-satellite Navigation Information Based on Inertial Assistance

Aiming at the application scenarios of the Global Navigation Satellite System (GNSS)/Strapdown inertial navigation system (SINS) integrated navigation algorithm for some special aircraft or some vehicles with high reliability requirements, this article selects two or more satellite navigation receivers to ensure satellite navigation For the reliable application of information, a dual-satellite navigation information optimization algorithm based on inertial assistance is designed. This algorithm designs navigation information availability criteria based on inertial information, navigation information tightening protection criteria, and two-way satellite navigation information selection criteria. On the one hand, it makes full use of inertial information, and on the other hand, it fully considers receiver performance indicators. Based on the principle of whoever locates first and use whoever is first, complete the optimal selection of dual-satellite navigation information sources, thereby improving the reliability and redundancy of satellite navigation information. Finally, the effectiveness of the information source selection algorithm is verified by simulation, and the algorithm can be promoted It is applied to the process of selecting the best use of the two information sources of guidance radar and seeker.