Abstract. A method for determining motion parameters of low-orbit spacecraft is presented. The approach is based on joint use of high-sensitive accelerometers measurement data and information from the satellite navigation equipment. Methodical aspects of the use of these high-sensitive accelerometers are considered for the case of the presence of navigation equipment measurements as well as for intervals of orbital parameters forecast. Estimated accuracy of definition and forecasting of orbital motion parameters of space vehicles with the use of proposed technique with the account for technical characteristics of highsensitive accelerometers are compared with results obtained with traditionally applied methods of navigating problems solution. Limitations are formulated for the field of high-sensitive accelerometers application in low-orbit spacecrafts to guarantee the accuracy of navigation problems solutions. The presented results confirm the possibility to improve the accuracy of solving the problems of navigational support of flight control of space vehicles and the quality of target information processing.

Keywords: low-orbit spacecraft, sensitive accelerometer unit, mass center movement parameters, atmospheric deceleration, determining and forecasting of spacecraft orbital motion parameters

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