THE SOLUTION OF THE PROBLEM OF THE SATELLITE AND INERTIAL NAVIGATION SYSTEMS INTEGRATION BASED ON THE NONLINEAR FILTERING THEORY
The close integration problem of the satellite navigation system and strapdown inertial navigation system is solved in the most generalized case. The peculiarities of the nonlinear algorithm of the navigation system's state vector estimation in consideration of continues nature of the inertial measurements and discrete character of the satellite ones are described. The method of the navigation problem general solution based on the nonlinear filtering theory is performed for the integrated navigation system. The method provides a high-precision determination of the object navigation parameters in the integrated mode and has durable characteristics in the mode of the inertial navigation system single functioning.