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   <subfield code="a">Integrated navigation system for a space vehicle on a geostationary or highly elliptic orbit operating in the presence of active jam</subfield>
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   <subfield code="c">[D. Kozorez, M. Krasil'shchikov, D. Kruzhkov, K. Sypalo]</subfield>
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   <subfield code="a">An onboard navigation system for a space vehicle on a geostationary or highly elliptic orbit including such measurement sources as optoelectronic Earth, Sun, and star trackers, and a multichannel global navigation satellite system receiver is studied. The purpose of this study is to form a general design of an integrated navigation system including the justification of its architecture and operation algorithms based on conditions under which the desired accuracy can be achieved. Based on the analysis of the GPS and GLONASS navigation satellites visibility conditions, the practicality of using a deeply integrated system architecture is established; this architecture can ensure the desired navigation accuracy even when less than four navigation satellites are visible. To integrate various measurements, a special &quot;scalar” modification of the Kalman filter (the so-called integral Kalman filter) is used. As uncontrollable factors, instrument sensor errors and artificial jam in the operation of the navigation signals receiver are considered. The main tool for the analysis of the navigation system error is simulation, which is performed using dedicated software of object-oriented architecture.</subfield>
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