An algorithm of inertial aided single satellite navigation with high dynamic

Under the conditions of the damage or loss of the satellite navigation system in the environment of war area or star exploration, the single satellite navigation can efficiently make up for the loss of navigation system. However, if the target is characterized with high dynamics, the error of single satellite navigation is far away from the practical demands. Thus, this paper proposed an algorithm of single satellite with high dynamics under the guidance of inertial navigation. And under the circumstance of high dynamics, we employ the inertial navigation component to get the coordinate offsets of the target, and utilize the pseudo-range difference of the integral Doppler measurement value and the inertial navigation system, use the fused filtering to obtain the location information in high dynamic conditions, and reach the location for target under the high dynamics. Comparing the algorithm proposed in this paper with the Doppler single satellite navigation and under the aid of pseudo range rate algorithm, we can conclude that at the speed of 100 m/s for the location targets, the position error is only 2% to the Doppler single satellite navigation algorithm and 3.5% to the pseudo range rate aided single position algorithm after 300 s, it can effectively provide positioning and navigation services for high dynamic positioning.