Aerospace Instrument-Making Annotation << Back ON THE ISSUE OF INCREASING THE CONTROL ACCURACY FOR THE SMALL SPACECRAFT I.A. Iskenderov, S.S. Baghirzade The main purpose of the research conducted in this article is the analysis and synthesis of methods to ensure the necessary accuracy of a small spacecraft control systems. As a result of the research, the current state of the problem solution was determined and the main disadvantages of the existing methods were revealed. Based on research it is clear that, filter Kalman used frequently to increase the accuracy of the control system on the spacecrafts has some disadvantages, which makes setting problem and increases computational burden despite effectiveness and power. The possibilities of alternative methods are currently being investigated, but this is not appropriate for the most computational burdens and accuracy. In comparison with other methods, especially with the filter Kalman, the use of filter Madgwick which does not have great calculation losses and is simpler to adjust, is considered as the most promising option to increase accuracy. It has been experimentally determined that this filter’s accuracy is not less than the filter Kalman and also has more stable parameters, which confirms that the filter Madgwick is used as one of the optimal methods, which can be used to increase the accuracy of the small spacecraft. Taking into account the features and capabilities in front of other existing filters today, the Madgwick filter was chosen based on a gyroscope, accelerometer and magnetometer, and the possibility of using this filter to improve the accuracy of attitude determination system, which is one of the most basic onboard control systems of the small spacecraft, was considered. In order to comparatively evaluate the performance of the Kalman and Madgwick filters, the models of these filters were studied in the MATLAB software environment. Keywords: small spacecraft; onboard control systems; MEMS-technology; filter Kalman; filter Madgwick; attitude determination system. DOI: 10.25791/aviakosmos.09.2019.862 Contacts: - Pp. 03-08.