TY - JOUR AU - Smyrnov, A.S. AU - Holubek, O. V. PY - 2023/02/23 Y2 - 2024/03/29 TI - IMPACT ANALYSIS OF MEMS-COMPONENTS ERRORS OF SINS ON ACCURACY OF SATELLITE LAUNCH VIA ULTRALIGHT LAUNCH VEHICLE JF - Journal of Rocket-Space Technology JA - Rocket-Sp. Tech. VL - 30 IS - 4 SE - Control systems, telecommunications, navigation and automation DO - 10.15421/452209 UR - https://rocketspace.dp.ua/index.php/rst/article/view/142 SP - 57-65 AB - The article is devoted to the development of work on the study of the influence of the error of measuring instruments of a strapdown inertial navigation system built using micro-electromechanical components on the accuracy of injection a spacecraft by an ultralight launch vehicle into low near-Earth orbits up to 400 km altitude and inclination order 37,4. For two modes of operation of a strapdown inertial navigation system (inertial and inertial-satellite), using the method of factorial analysis, a study was made of the accuracy of the injection of the spacecraft, as a result of which the following results were obtained. The determining disturbing factors are revealed, the dependencies of the trajectory tubes and the limit deviations of the kinematic parameters of the spacecraft at the point of separation from the launch vehicle on the altitude of the target orbit are determined. It is revealed that the determining disturbing factors are the run-to-run bias of the gyroscope and the random drift of the gyroscope. It is shown that the trajectory tubes increase in size with the flight time and with an increase of the altitude of the orbit. The maximum deviations of the current position and absolute speed in the inertial mode were 218 km and 543 m/s, respectively. In the inertial satellite mode, these values do not exceed 132 m and 1.4 m/s, respectively. It is determined that the maximum deviations of the osculating parameters of the spacecraft orbit are: in altitude is 54 km, in inclination is 1.7, in eccentricity is 1.210-4, in right ascension ascending node is 6.9. For the inertial-satellite mode: in height is 722 m, in inclination is 0.003, in eccentricity is 2.310-4, in right ascension ascending node is 0.03. It is shown that the use of data from a satellite navigation system significantly reduces the trajectory tube and increases the accuracy of the osculating parameters of the spacecraft orbit. A comparative analysis of the spacecraft injection accuracy was carried out for two values of the inclination of the target orbit of the spacecraft 37,4 and 51,5. ER -