Aerospace Instrument-Making Annotation << Back NAVIGATING ALGORITHMS OF THE INTEGRATED INERTIAL-SATELLITE SYSTEMS ON THE BASIS OF SPATIAL MODELS OF MOVEMENT S.V. Sokolov, S.S. Vdovichenko Modern algorithms integration strapdown inertial navigation system (SINS) and satellite navigation systems (SNS), which use differential or object model or equation error INS require a priori information about the trajectory of the object at the time that for most objects is only possible in small time intervals. This leads to significant errors or inertialsatellite systems in their integration, or the rapid divergence of the filtering process with the loss of satellite communications. At the same time, to navigate a wide class of objects (launch vehicles, satellites, air transport, etc.), moving on a preknown highprecision spatial trajectories may use spatial models of the way, greatly simplifies the navigation. The paper shows that the use of such spatial models do not require linearization navigation equations (as in the construction of equations errors INS), increasing positioning accuracy, reduces the dimension of the vector of the estimated navigation parameters, reducing the computational costs, enhances observation vector, allowing a fundamentally solve the problem of a posteriori estimation of motion parameters autonomous measuring devices with the loss of satellite communications. As spatial models considered depending longitude and altitude trajectory of latitude. This allows the failure of satellite communications in addition to use the testimony of one of the three accelerometers SINS as a signal independent of the observer motion parameters of the object to the construction of a nonlinear stochastic filter navigation vector. In the presence of satellite measurements with appropriate aggregation of their autonomous (accelerometer measurements), but in this case, the filtering algorithm is formed as a continuousdiscrete, taking into account the continuous nature of the change navigation parameters and discrete – satellite measurements. A numerical simulation of this algo-rithm both for tight coupling SINS and SNS, and with the loss of satellite communications is realized. The simulation results suggest the possibility of the effective use of the proposed approach, which implements all the advantages mentioned above. Key words: navigation algorithms, the tight coupling inertial-satellite systems, spatial models of a trajectory. Contacts: E-mail: s.v.s.888@yandex.ru Pp. 36-45.