novtexmechМехатроника, автоматизация, управлениеMekhatronika, Avtomatizatsiya, Upravlenie1684-64272619-1253Commercial Publisher «New Technologies»10.17587/mau.24.107-112novtexmech-1322Research ArticleДИНАМИКА, БАЛЛИСТИКА И УПРАВЛЕНИЕ ДВИЖЕНИЕМ ЛЕТАТЕЛЬНЫХ АППАРАТОВDYNAMICS, BALLISTICS AND CONTROL OF AIRCRAFTАлгоритмы комплексирования инерциальной навигационной системы с датчиками угловых ускоренийAlgorithms for Complexing an Inertial Navigation System with Angular Acceleration SensorsНеусыпинК. А.NeusypinK. A.

д-р техн. наук, проф., зав. кафедрой

Москва

Moscow

neysipin@mail.ruПролетарскийА. В.ProletarskyA. V.

д-р техн. наук, проф., декан

Москва

Moscow

pav_mipk@mail.ruСелезневаМ. С.SeleznevaM. S.

канд. техн. наук, доц.

Москва

Associated Professor of the Department "Informatics and Control Systems", Bauman Moscow State Technical University, Cand. of Tech. Sc.

Moscow

m.s.selezneva@mail.ruМГТУ им. Н. Э. БауманаРоссияDepartment of Informatics and Control Systems Bauman Moscow State Technical UniversityRussian Federation202306022023242107112Copyright © Commercial Publisher «New Technologies», 20232023Commercial Publisher «New Technologies»Commercial Publisher «New Technologies»https://mech.novtex.ru/jour/about/submissions#copyrightNoticehttps://mech.novtex.ru/jour/article/view/1322

Исследована задача повышения точности платформенной инерциальной навигационной системы летательного аппарата в условиях отсутствия высокоточных дополнительных датчиков информации, например GPS. Предложено установить на гиростабилизированную платформу инерциальной навигационной системы датчики угловых ускорений. Использование сигналов с датчиков угловых ускорений позволило сформировать сигналы коррекции для инерциальной навигационной системы. Разработаны алгоритмы коррекции в структуре инерциальной навигационной системы и в ее выходном сигнале. Эффективность разработанных алгоритмов продемонстрирована с помощью полунатурного моделирования с инерциальной навигационной системой Ц060К.

In this paper the problem of increasing the accuracy of inertial navigation system of an aircraft in the absence of high-precision additional information sensors, such as GPS, has been studied. It is proposed to install angular acceleration sensors on the gyrostabilized platform of the inertial navigation system. The use of signals from the angular acceleration sensors made it possible to generate correction signals for the inertial navigation system. Correction algorithms have been developed in the structure of the inertial navigation system and in its output signal. The effectiveness of the developed algorithms has been demonstrated using semi-natural simulation with the Ts060K inertial navigation system.

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The authors declare that there are no conflicts of interest present.