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The centralized Kalman filter is always applied in the velocity and attitude matching of Transfer Alignment (TA). But the centralized Kalman has many disadvantages, such as large amount of calculation, poor real-time performance, and low reliability. In the paper, the federal Kalman filter (FKF) based on neural networks is used in the velocity and attitude matching of TA, the Kalman filter is adjusted by the neural networks in the two subfilters, the federal filter is used to fuse the information of the two subfilters, and the global suboptimal state estimation is obtained. The result of simulation shows that the federal Kalman filter based on neural networks is better in estimating the initial attitude misalignment angle of inertial navigation system (INS) when the system dynamic model and noise statistics characteristics of inertial navigation system are unclear, and the estimation error is smaller and the accuracy is higher.

For the rapid response of the aircraft, it is required that the aircraft is not only quick but also chooses the shortest flight routes. The great circle track is the shortest flight route on the earth between any two points, but the great circle track needs to cross the polar region when the aircraft flies over the hemispheres of East and West. Because the polar region has some particularity, such as the landform characteristics, the climatic conditions, and the vast territory, the transpolar aircraft is the key technology of global navigation. This article researched on the algorithm of SINS/GPS integrated navigation system and analyzed the result of simulation when the SINS/GPS integrated navigation system works in the middle-and low-latitude region and the polar region. The result of simulation shows that the working performance of SINS/ GPS integrated navigation system is improved and makes use of their respective advantages to overcome the shortcomings. By comparing the result of simulation, the navigation precision is consistent when the SINS/GPS integrated navigation system works in the middle-and low-latitude region and the polar region.

Because the accuracy of the existing airborne navigation is lacking in the polar region, it is difficult to ensure the safety and reliability of the aircraft when it is flying over the polar region. The integrated navigation system based on the inertial navigation technology uses multi-information fusion to assist collaborative navigation and obtain an indirect grid navigation algorithm that combines the azimuth navigation algorithm and the grid navigation algorithm to solve the existing problems. This paper analyzes the principle of the inertial navigation system in the polar region, the semiphysical simulation experiments are carried out by using the navigation theory and the background engineering, and the accuracies of the integrated navigation system of the indirect grid frame in the polar region and the integrated navigation system in the middle and low latitudes are consistent, which verifies the feasibility and effectiveness of the SINS/CNS/GPS integrated navigation system in the polar region. In addition, the paper provides the theoretical basis and the application of engineering to achieve the SINS/CNS/GPS integrated navigation system in the polar region.

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