Fedoskin O.I., Kashkarov A.S.

Space vehicle deduction into a target orbit should be implemented with accuracy required by the customer. In this connection, at decision-making on actuation of particular measuring unit of a strapdown inertial navigation measuring unit in a structure of an onboard control system of the accelerating unit it is necessary to consider potential accuracy of deduction of a space vehicle into a target orbit. In the article, outcomes of research of potential navigation accuracy of the accelerating unit are reduced at deduction of paying loads with the use of standard 9.hour injection trajectories. The problem is decided in linear statement. The research method is based on the use of sensitivity functions. The basis of the analysis of accuracy of deduction of the accelerating unit executed in the present activity on scheduled orbits is the method of numerical modelling. The task in view was decided by tools of the system Simulink - entering in software package MATLAB - of firm MathWorks, Inc. At modelling, three approaches were used: the simplified one, guaranteeing one, and statistical analysis. The research has shown that at introduction of a unique source of the approach-correcting information, the use of satellite navigation systems by is the most effective. At the same time, the maximum accuracy of navigating information is provided the complex navigating system using both satellite tools of correction and star trackers.