METHODOLOGY OF DESIGNING AN INTEGRATED LOOP FOR TERMINAL GUIDANCE AND INERTIAL-SATELLITE AIDED NAVIGATION IN CONTROL SYSTEMS OF SPACE LAUNCH VEHICLES - THE ANALYSIS OF FULL-SCALE TESTS

摘要

Specific features of application of the Information-Insurance Technology previously offered for control objects with increased requirements for information reliability are described. It is shown that the measures intended to provide the validity check of the integrated navigation system output data that involve the measurements from the GLONASS/GPS receiver and the need for their accumulation before they are used in the terminal guidance loop require that these factors be taken into account in the statement of the control problem. The realization of the adopted solutions results in a problem of working-off during the final stage of an active leg of saltatory disturbances represented in the form of accumulated and detected errors in coordinates and velocity components of a navigation trajectory. It is shown that this problem is a priori equivalent to unpredictable retargeting during the flight. The problem of retargeting occurs for the first time in the practice of space launch vehicles. The analysis of accuracy and functioning of the integrated system of upper-stage (US) "Fregat" is carried out. In particular, the results of working-off of the previously mentioned disturbance types in normal and lateral stabilization systems are represented.